@A318/A319/A320/A321

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 71

TITLE: POWER PLANT GENERAL - AFT ENGINE MOUNT INSTL - INSPECTION

OF AFT ENGINE MOUNT INNER RETAINER BRACKET FOR CFM56-5A/-

5B ENGINES.

MODIFICATION No.: None

This page transmits Revision No.01 of Service Bulletin No.A320-71-1060

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 01 issued to change COMPLIANCE from Recommended to Mandatory, to update the

MPD repercussion and to extend the effectivity for newly delivered aircraft.

CHANGES

The main changes of this revision are:

- COMPLIANCE changed from Recommended to Mandatory,

- MPD Task reference deleted,

- Inner, Center and Outer Retainer Brackets changed by Left, Center and Right Retainer Brackets,

- References to SUBTASKS corrected,

- Units of measure to tight the nut Item (14) corrected (lbf.in. instead of lbf.ft),

- Fig. A-FRAAA (Inspection Report) added,

- Fig. A-FBBAA and A-FAAAA corrected,

- Effectivity updated,

- Minor changes applied.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

SUMMARY

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

REASON UPDATED R

GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R

EFFECTIVITY OPERATOR LIST UPDATED R

MANPOWER MANPOWER UPDATED R

MANPOWER UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

CONF 002 CONFIGURATION DEFINITION UPDATED R

REASON

History HISTORY UPDATED R

COMPLIANCE

Classification CLASSIFICATION UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

APPROVAL APPROVAL UPDATED R

MANPOWER MANPOWER UPDATED R

MANPOWER UPDATED R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED

CONFIGURATION UPDATED

R

PUBLICATIONS AFFECTED DELETED FOR

APPLICABLE MSN

D

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED R

LIST OF MATERIALS - OPERATOR

SUPPLIED

Equipment

Equipement BFEA01 PART MATERIAL SET UPDATED R

TOOLING

Tools TOOLS UPDATED R

ACCOMPLISHMENT INSTRUCTIONS

TASK 711060- 832-801-001-Detailed

Inspection of the Aft Engine Mount Inner

Retainer Brackets for Engine 1 and

Engine 2

TASK SOLUTION UPDATED

TASK TITLE UPDATED

NOTE UPDATED

CAUTION UPDATED

R

Subtask 711060-941-001-001 SUBTASK SOLUTION UPDATED R

Subtask 711060-941-002-001 SUBTASK SOLUTION UPDATED R

Subtask 711060-941-001-001 SUBTASK SOLUTION UPDATED R

Subtask 711060-941-002-001 SUBTASK SOLUTION UPDATED R

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 711060-832-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

NOTE UPDATED

R

Subtask 711060-832-002-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

NOTE UPDATED

R

Subtask 711060-000-003-001 SUBTASK SOLUTION UPDATED R

Subtask 711060-000-004-001 SUBTASK SOLUTION UPDATED R

Subtask 711060-000-005-001 SUBTASK SOLUTION UPDATED R

Subtask 711060-000-006-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 711060-400-001-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-400-003-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-400-004-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-400-002-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-400-005-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-400-006-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-831-001-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 711060-832-001-002 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

NOTE UPDATED

R

Subtask 711060-832-002-002 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

NOTE UPDATED

R

Subtask 711060-000-003-002 SUBTASK SOLUTION UPDATED R

Subtask 711060-000-004-002 SUBTASK SOLUTION UPDATED R

Subtask 711060-000-005-002 SUBTASK SOLUTION UPDATED R

Subtask 711060-000-006-002 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 3

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 711060-400-001-002 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-400-003-002 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-400-004-002 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-400-002-002 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-400-005-002 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-400-006-002 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 711060-831-001-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 711060-942-001-001 SUBTASK SOLUTION UPDATED R

Subtask 711060-942-002-001 SUBTASK SOLUTION UPDATED R

Subtask 711060-942-001-001 SUBTASK SOLUTION UPDATED R

Subtask 711060-942-002-001 SUBTASK SOLUTION UPDATED R

Fig. A-FBAAA FIGURE SOLUTION UPDATED R

Fig. A-FBAAA Sheet 01 SHEET UPDATED R

Fig. A-FBBAA FIGURE SOLUTION UPDATED R

Fig. A-FBBAA Sheet 01 SHEET UPDATED R

Fig. A-FFAAA

Fig. A-FFAAA Sheet 01 SHEET UPDATED R

Fig. A-FFAAB

Fig. A-FFAAB Sheet 01 SHEET UPDATED R

Fig. A-FRAAA FIGURE SOLUTION ADDED N

Fig. A-FRAAA Sheet 01 SHEET ADDED N

Fig. A-FRAAA Sheet 02 SHEET ADDED N

Appendix 01 - Elapsed Time Assumption

APPENDIX CONTENT APPENDIX CONTENT UPDATED R

Fig. A-FAAAA

Fig. A-FAAAA Sheet 01 SHEET UPDATED R

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

No previous revision

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 4

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

REVISION SEQUENCE

ORIGINAL: Oct 09/14

REVISION No. : 01 - Apr 07/15

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 5

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 6

5

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 71

TITLE: POWER PLANT GENERAL - AFT ENGINE MOUNT INSTL - INSPECTION

OF AFT ENGINE MOUNT INNER RETAINER BRACKET FOR CFM56-5A/-

5B ENGINES.

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During scheduled inspections, some operators have reported damage on the Aft Engine Mount Inner

Retainer Brackets fitted on A320 Family Aircraft powered by CFM56-5A/-5B engines.

The Inner Retainer Bracket provides a locking feature to the two nuts of the inner and outer pins

attaching the Aft Links to the Aft Mount Beam (also named Aft Engine Mount). The same Retainer is

used for the three Link Assemblies of the Aft Engine Mount. In case of broken Inner Retainer Bracket,

the locking feature is lost and knowing that these Nuts are not self-locked, they could become loose.

Subsequently, the Pins can also loosen and the Aft Mount Link would be no longer secured to the Aft

Engine Mount. In this condition, the certification loads cannot be sustained anymore.

The outcome of investigations confirmed that the Retainer damage is due to the fatigue cracking

mechanism resulting from the dynamic effect of Engine vibrations.

On March 2013, the Alert Operators Transmission (AOT) A71N001-12 and UTAS Service Bulletin No.

RA32071-146, rendered mandatory by EASA Airworthiness Directive (AD) No. 2013-0050, requested

one time inspection for damaged Inner Retainer Brackets and the replacement of nonconforming "Dull"

surface finish Retainers by the "Bright" surface finish Retainers. The nonconforming "Dull" surface finish

was more prone to pitting corrosion and which facilitated crack initiation.

However the main cause of crack initiation remains the vibration dynamic effect that affects both

Retainers with "Dull" and "Bright" surface finishes. The nonconforming "Dull" surface’s pitting corrosion

is an aggravating factor.

In addition the UTAS Service Bulletin No. RA32071-160 was published to advise repetitive inspections

of the affected Aft Engine Mount Retainer Brackets.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 1

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@A318/A319/A320/A321

SERVICE BULLETIN

SUMMARY

This Inspection Service Bulletin details a periodic inspection of the Aft Engine Mount Retainers to be

accomplished within the threshold and interval mentioned in the PLANNING INFORMATION paragraph

1.E.

Accomplishment of this Inspection Service Bulletin will allow an early detection of any potential damage

on the Aft Mount Retainers and will avoid additional heavy maintenance operation. This repetitive

inspection is required up to the availability of the final fix solution.

The operational/maintenance consequences of this Service Bulletin are covered by the update of the

affected publications included in the PLANNING INFORMATION paragraph 1.K.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Equipment BFEA01 1 See SB Inner Retainer Bracket

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Equipment BFEA01 1 See SB Inner Retainer Bracket

EFFECTIVITY

**CONF ALL

This Service Bulletin is applicable to this (these) operator(s) :

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 2

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SERVICE BULLETIN

SUMMARY

07P 11S 15T 16T 17R 17S 17W 27V 31P 31V 32Q 35T 35U

36R 40S 41S 43S 47P 52T 59Z 61W 69X 73W 74T 76W 79W

80X 83Q 83V 85T 85U 86Z 89T 90Q 91X 95W 98W AAF AAL

AAW AAY ABQ ABY ACA ADH AFL AFR AHY AIB AIC AIJ AJD

ALK AMC ANA ANR AOJ APJ ART AUA AVA AWM AXM AZA B2V

BAW BEC BEL BER BGF BGH BHP BIE BJN BSX BTK BTN C2C

C8J C9G CAA CBJ CCA CCM CDC CEB CEF CES CFG CHB CIB

CQH CQN CRK CSA CSC CSN CSZ CTN CTV CUA DAL DAT DCS

DKH DLH DNV DQA DRK EDW EIN ETD ETJ EVA EVE EWG EZY

F2I FFT FHY FIN FLI FPY FRN FTZ G2X G4I G8E GAP GCR

GFA GHT GIA GLG GMI GOW GSW GWI HKE HKJ HRM I2L IAC

IAW IBE IBS IND IRA ISS IZG JAD JAS JAV JZR KAC KAY

KGL KKK KNE LAA LAN LAO LBT LIM LJB LKE LLC LLM LLP

LWA LZB MAC MAU MEA MJF MJN MLD MLM MMA MON MOV MSC

MYX NLY NMB NVD NWS OAW OBS ONE PAL PGT PIA PKZ PTI

QAF QDA R1T RBG RCT RFJ RJD ROT ROU RYW RZO SBI SDM

SFJ SFW SHU SKU SMX SND SNX SOL SUD SVA SVR SVW SWM

SWR SYA TAE TAI TAM TAP TAR TBA TBJ TCW TCX THY TJS

TSO TVS TXP UAE UEA UJX UKN UNA USA UTA UZB VJC VKG

VLE VLG VNL VRD VRE VVC WHT WOW WRC

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT A71N001-12

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 711060-832-801-001: Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets

for Engine 1 and Engine 2

TOTAL MANHOURS 9.50

ELAPSED TIME (HOURS) 1.50

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 3

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SERVICE BULLETIN

SUMMARY

**CONF 002

Task 711060-832-801-001: Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets

for Engine 1 and Engine 2

TOTAL MANHOURS 9.50

ELAPSED TIME (HOURS) 1.50

APPENDICES

**CONF ALL

Appendix 01 - Elapsed Time Assumption

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 4

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SERVICE BULLETIN

SUMMARY

**CONF ALL

A

A A

LH SHOWN

RH SYMETRICAL

B

TYPICAL

B

PART TO BE INSPECTED

N_SB_711060_5_SAAA_01_00

Figure A-FSAAA - Sheet 01

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 5

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SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 6

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Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 71

TITLE: POWER PLANT GENERAL - AFT ENGINE MOUNT INSTL - INSPECTION

OF AFT ENGINE MOUNT INNER RETAINER BRACKET FOR CFM56-5A/-

5B ENGINES.

MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

NOTE: This Service Bulletin is applicable only to aircraft equipped with CFM56-5A

and CFM56-5B engines.

(1) Models

318-111 318-112 319-111 319-112 319-113 319-114 319-115 320-211

320-212 320-214 320-216 321-111 321-112 321-211 321-212 321-213

(2) Effectivity by MSN

0029 0059 0068-0073 0078 0083-0088 0093-0094 0104 0110-0112 0115-0119

0121-0127 0135 0137-0138 0140-0142 0148-0150 0152-0154 0157-0162 0167

0171-0176 0181-0183 0185 0189-0190 0192 0195 0197 0199-0203 0205-0214

0216-0220 0224 0229 0231-0235 0237 0239-0242 0244 0248 0253-0255 0262-0270

0272-0274 0277 0279 0281-0282 0284-0285 0287 0289-0290 0293-0294 0297-0298

0300-0303 0306-0307 0309 0311-0312 0318-0319 0323-0325 0328-0331 0333

0339-0343 0345-0346 0350 0355-0356 0358-0360 0367 0370-0372 0378 0380-0383

0387-0388 0390-0391 0395 0399-0404 0407-0410 0413 0417-0422 0426-0427 0434

0436 0438 0445 0459 0466 0477 0482 0488 0491 0495 0497-0498 0501 0507 0509

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 1

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SERVICE BULLETIN

0511 0513-0517 0519-0522 0524-0526 0528-0529 0531-0535 0537 0541 0544-0546

0548-0549 0552-0554 0559 0562 0566 0569-0570 0572 0574 0576-0579 0581 0583

0585-0586 0588 0593-0594 0596 0598-0600 0603 0605 0607-0612 0616-0619

0621-0623 0625 0627 0629-0630 0634-0637 0639 0641-0651 0653-0654 0656-0658

0660 0662 0664-0666 0669-0673 0675 0677 0679 0681-0682 0684-0685 0688-0689

0691 0693-0695 0697 0700-0701 0703 0706-0707 0711 0713-0714 0716-0717 0719

0721 0723-0724 0726-0730 0732 0734-0738 0740 0742 0744-0745 0749-0750 0752

0754-0755 0757 0761 0763-0769 0773-0779 0781-0782 0785-0786 0790 0793-0797

0799-0801 0807-0809 0813-0815 0817-0819 0821 0823 0827-0833 0837-0838

0840-0841 0844-0846 0848 0852-0854 0860-0861 0863 0868-0870 0875-0876

0879-0880 0883-0885 0888 0890-0891 0894 0896-0897 0903-0907 0909 0911 0914

0917 0920-0923 0925-0926 0929 0933 0935-0942 0945-0947 0949 0951 0957-0962

0964 0967 0970-0973 0975 0978-0979 0981-0982 0984-0988 0991-0992 0994-1000

1002 1005-1006 1009 1011-1012 1016-1021 1023 1025-1030 1033-1034 1036-1038

1040-1041 1046-1048 1051-1052 1054-1055 1058-1059 1061-1063 1065 1067-1073

1077-1078 1081 1084 1086-1087 1089-1091 1093-1095 1097 1099-1102 1106-1109

1112 1114 1119-1122 1124-1127 1129-1138 1141 1144-1145 1147-1152 1154-1155

1157 1160 1162 1164-1165 1167-1172 1175-1176 1179-1182 1184-1185 1187

1189-1191 1198 1200-1201 1203 1205-1206 1208-1210 1213 1216-1217 1219-1221

1224 1226 1229-1231 1233 1237-1238 1241-1242 1244-1245 1247 1249-1250 1252

1254-1255 1259 1262-1265 1267-1269 1271 1275 1277 1283 1285-1289 1292 1294

1296-1299 1301 1303 1305-1320 1322 1324-1326 1328 1330-1331 1336-1337 1340

1342 1344-1348 1352 1354 1357-1358 1360-1362 1364-1365 1367 1369-1372

1377-1379 1381-1382 1385-1394 1396 1399 1402-1405 1412-1417 1425 1429-1431

1434 1436-1437 1439 1441-1444 1447-1451 1453-1458 1461-1462 1465 1467

1470-1473 1476 1478-1481 1483-1485 1488-1489 1492-1494 1496 1498-1499

1501-1505 1515-1517 1519-1521 1524-1525 1530-1532 1535-1536 1539-1544

1549-1551 1553-1554 1556 1560 1562 1564 1567 1570-1572 1577-1579 1582-1583

1588 1592 1597-1599 1601-1603 1605 1607 1611-1612 1615-1616 1618 1622-1623

1625 1629-1630 1632-1634 1637-1641 1645-1646 1651 1654-1655 1657-1659 1662

1666-1668 1673-1674 1677-1679 1681 1683-1686 1691-1694 1699-1701 1704 1706

1709 1712-1714 1716-1720 1722 1724-1726 1733 1735-1736 1738 1740 1742-1748

1750-1753 1756-1757 1759 1761-1762 1765-1767 1769-1770 1772 1774-1775

1777-1781 1783 1786-1787 1789 1791 1793 1795-1797 1799-1800 1803 1805-1806

1808-1812 1815-1816 1819-1820 1824 1828 1833 1836 1838-1839 1841 1846

1851-1853 1859-1860 1863-1864 1866-1867 1870 1872-1876 1879 1881-1882

1884-1887 1889-1890 1894 1897 1900-1901 1905-1906 1908 1911 1913 1916

1920-1921 1923-1925 1929 1931-1932 1936-1938 1940 1942-1943 1949 1951 1954

1959-1961 1963-1966 1968 1972-1973 1975-1976 1978 1980-1983 1988-1990 1994

1997 1999 2001-2003 2005 2009-2013 2018-2019 2022 2024 2026 2028 2030

2033-2037 2039 2043 2046-2050 2052-2054 2056-2057 2059-2062 2064-2066

2068-2069 2071-2072 2074 2076 2078 2081-2083 2086-2087 2091-2093 2095

2100-2101 2103-2104 2106 2109 2113-2117 2119-2120 2122-2124 2126-2127 2129

2131 2133-2134 2140 2142-2146 2151 2154-2155 2158 2162-2163 2165-2166

2170-2171 2174-2176 2178-2184 2186-2187 2189 2191 2196 2198-2199 2206-2209

2212-2214 2217 2219-2222 2224-2225 2227-2228 2230 2233 2235-2237 2239-2245

2248-2251 2253 2256 2258 2260 2262 2264-2266 2269-2272 2274 2278-2279 2283

2285 2287 2289 2291 2293-2294 2298 2300 2306 2309 2311 2315 2317-2319 2325

2327-2328 2330 2332-2333 2337 2342 2344 2346-2347 2349-2350 2353-2354

2357-2358 2360-2361 2364-2365 2367 2369-2370 2373-2374 2377-2378 2380-2382

2385 2387-2388 2390-2392 2394 2398-2400 2402 2406-2407 2409 2411-2412 2416

2419-2420 2425 2427 2432 2436-2437 2439-2440 2442 2446 2448 2450-2451 2456

2460 2463-2465 2471-2472 2474 2477-2478 2481 2483-2484 2486-2488 2492-2495

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 2

5

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SERVICE BULLETIN

2497-2499 2503 2506-2508 2511-2512 2514 2516 2518-2519 2523 2525 2527-2529

2532 2538-2552 2554-2558 2561-2563 2565 2569 2575 2578 2581-2584 2586 2588

2591-2593 2596 2599 2601 2605-2607 2611-2612 2616-2620 2623-2625 2627-2629

2632-2633 2635-2638 2641 2644 2646 2652 2654 2656 2658 2662 2665 2668 2672

2674-2675 2677-2678 2681 2683-2686 2691 2693 2695-2696 2699-2700 2702

2705-2709 2712 2715-2716 2719 2721 2726-2727 2729 2733 2735-2736 2740

2742-2746 2748-2751 2754 2756-2758 2760-2765 2768-2770 2773-2774 2776-2779

2782 2785-2786 2788-2790 2792 2794-2796 2798 2800-2801 2803 2805-2807

2810-2812 2816 2818-2822 2824-2827 2829-2831 2834-2837 2839 2841-2843

2846-2847 2849 2851-2855 2857 2860-2861 2865-2867 2869-2870 2873 2875-2879

2881-2882 2884-2885 2889-2891 2895 2897 2899 2902-2903 2905 2907 2909-2910

2912-2913 2915 2918 2920-2921 2923-2926 2930-2932 2935 2937-2939 2944

2946-2947 2949-2951 2954-2957 2959-2962 2964-2968 2972-2973 2975 2980

2985-2986 2988-2989 2991 2993-2996 2998 3000 3002-3003 3006 3008-3009 3014

3016 3018-3019 3021 3023-3025 3027-3028 3031 3035-3037 3040-3041 3043-3044

3046-3048 3051-3056 3058-3061 3063-3065 3068 3070 3073 3076 3078-3080

3082-3085 3087-3088 3090 3093-3102 3107-3109 3111 3115 3117-3118 3121-3123

3129-3140 3145-3149 3151-3155 3157 3160-3161 3164 3168-3171 3173-3174 3176

3178-3182 3184 3186-3189 3191 3194 3197 3199 3201-3206 3209 3211-3213 3215

3218 3220-3221 3223-3226 3230 3232-3234 3236-3238 3240 3242-3243 3245-3247

3249-3250 3255-3256 3260-3262 3266-3268 3271-3273 3277-3278 3281-3282

3284-3286 3288-3289 3291 3293 3295 3298-3300 3304-3307 3309-3310 3312-3313

3318 3320-3321 3323-3329 3331 3333-3334 3336-3338 3340 3343-3347 3349 3353

3356 3359 3361-3364 3366-3368 3370 3372-3374 3376-3377 3380 3383 3385

3388-3389 3391 3394 3396 3398-3401 3403-3404 3406-3408 3410-3413 3415 3417

3419-3420 3422 3425-3427 3431-3433 3435-3436 3440-3448 3452 3455-3456

3460-3461 3464-3467 3470-3473 3475-3477 3480 3482 3485-3487 3489-3490 3492

3494 3498 3501-3506 3508 3511 3513-3516 3518 3521 3523 3528-3530 3532-3533

3536-3537 3540 3542 3544-3545 3549 3551 3553 3555 3557 3559-3560 3563-3565

3568-3569 3571 3573-3574 3576 3579 3582 3584 3586 3589 3593-3594 3596-3599

3601 3604-3605 3608-3612 3615-3617 3619-3620 3623 3626-3634 3639-3640

3643-3644 3646-3648 3651-3653 3655-3658 3660-3662 3664-3667 3670 3675

3678-3679 3682-3684 3686-3687 3689-3691 3695-3696 3698-3702 3704 3706 3708

3711 3715 3720 3722-3723 3725 3727-3729 3731-3733 3735 3739 3742 3744

3746-3747 3749-3752 3754-3756 3758 3762-3763 3765-3767 3769 3774 3776-3778

3780-3781 3786-3792 3794-3795 3798-3799 3802 3805-3806 3808-3810 3813-3815

3817-3819 3822-3828 3830-3831 3833-3835 3838 3840 3843-3846 3848 3852-3857

3859 3861 3865-3866 3868 3871-3872 3874-3875 3879-3880 3882-3889 3891-3892

3894-3896 3898 3900 3903 3905-3909 3913 3915 3918-3919 3921-3923 3925 3928

3930-3933 3939-3940 3942 3945-3946 3949-3950 3952-3957 3961 3963 3967

3970-3976 3978-3980 3983-3985 3988 3991-3992 3994-3995 3997-3998 4001-4002

4004 4006-4007 4009-4015 4019-4022 4024 4026 4028-4035 4038-4040 4046

4048-4049 4051-4052 4055-4059 4061-4064 4069-4072 4074-4076 4078-4081

4083-4084 4086-4093 4095-4106 4108 4115-4117 4119-4122 4125-4129 4131-4133

4135 4137-4139 4141 4143 4145-4150 4152-4155 4157-4162 4164 4167-4169 4172

4175 4179-4180 4182 4187-4188 4190-4191 4193-4196 4199-4205 4207-4208

4211-4212 4218-4219 4221-4222 4226 4228 4231 4233-4237 4241-4244 4249-4251

4253-4255 4258 4261 4263 4267-4269 4272-4276 4278 4280-4281 4283-4284

4286-4287 4289 4291 4293-4295 4298 4302 4304 4307 4310 4313-4314 4316 4318

4320 4322 4324-4325 4327 4329 4331-4338 4344-4347 4349 4353 4357 4361-4369

4371 4373 4375-4377 4379-4381 4385-4386 4390-4399 4401-4402 4404-4405 4408

4411 4414-4419 4425-4427 4429 4432-4433 4437-4438 4441-4442 4444 4446-4451

4453-4456 4458 4461-4463 4465 4467-4468 4470 4472 4475 4477-4478 4480

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 3

5

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SERVICE BULLETIN

4484-4487 4489-4490 4492 4494 4498-4504 4507-4508 4510-4512 4517 4519-4521

4523-4524 4526 4528 4534 4536-4539 4541-4542 4544 4547 4550 4554-4559 4562

4564-4565 4567-4568 4571-4574 4577 4579 4581-4582 4586-4591 4594 4596

4599-4601 4604 4606 4610-4611 4613 4616 4618 4622-4625 4627 4631 4634-4636

4639-4641 4646 4648-4652 4655-4656 4658-4659 4661 4663-4664 4667-4668 4671

4673-4676 4678-4681 4684-4685 4688-4689 4691-4694 4699 4702 4704-4705

4708-4709 4711-4715 4717-4718 4720-4724 4727-4730 4732-4735 4738 4740

4742-4745 4747-4750 4756 4758-4760 4763-4770 4776-4778 4780-4781 4785 4787

4789 4793-4797 4799-4801 4803 4805-4809 4811 4814-4816 4820-4823 4827 4829

4831 4833 4835 4837-4841 4844 4846 4848-4849 4851-4852 4854-4855 4857

4859-4862 4865 4867 4869-4871 4875-4878 4880 4882 4886-4887 4889-4892

4894-4896 4900-4901 4903 4907-4910 4913 4915 4917 4921 4924-4925 4927-4928

4933 4936-4939 4941-4943 4946 4948 4952-4953 4955-4956 4958-4959 4962-4964

4967 4969-4970 4972 4974 4978-4981 4983-4985 4987-4989 4991 4993 4999 5001

5003-5009 5012-5020 5022-5023 5026 5031-5034 5037-5038 5040 5044-5048

5051-5052 5056-5059 5063-5067 5069-5072 5079 5081-5082 5084-5086 5088

5096-5098 5100-5104 5106-5117 5119 5122 5125-5126 5129-5131 5133-5134

5136-5138 5140 5143 5146-5147 5149-5150 5152-5153 5157 5162-5163 5165-5167

5171-5172 5174-5175 5178-5179 5181 5184 5187 5189 5191 5193 5195 5200-5201

5203-5204 5206 5209 5213 5215-5216 5220-5224 5226 5229 5232 5234 5236

5238-5240 5243 5246 5249-5250 5252-5253 5256 5260 5263-5264 5266 5271-5273

5276-5278 5283-5285 5289-5290 5293-5295 5299 5304 5307 5310 5314-5316

5318-5320 5324-5325 5327-5331 5333 5338-5339 5341-5342 5344 5347 5351

5353-5354 5356 5358-5360 5364 5366 5369 5371-5373 5377-5381 5383-5384 5386

5393-5394 5396-5400 5403 5405 5408 5412 5414-5416 5419-5421 5423-5425 5428

5430-5431 5434-5435 5440-5448 5451-5455 5463-5464 5466 5468 5471 5474-5475

5477-5478 5483 5485-5487 5491 5493-5494 5497-5498 5501-5502 5504-5505 5509

5511-5515 5518 5521-5522 5525-5527 5529 5533 5536 5538 5540-5542 5544-5545

5547-5552 5554 5556-5557 5559-5560 5562-5563 5565 5567-5568 5570-5574 5576

5578 5580-5581 5583 5585-5594 5597 5601 5603 5607 5610 5614 5616 5619

5621-5622 5625-5627 5630 5632 5635 5638-5640 5642-5644 5648 5652-5654

5656-5659 5661 5664-5666 5668-5669 5673-5675 5678-5679 5681 5684 5686-5688

5690-5694 5696 5698 5702-5704 5706-5707 5710 5716 5718-5720 5722 5724 5726

5729-5731 5733 5735 5737 5739-5743 5745-5746 5748-5749 5752-5755 5757

5759-5762 5764 5766 5768-5769 5771-5773 5777-5779 5781 5785-5786 5788-5790

5792 5798-5799 5801-5802 5808-5812 5815-5816 5818 5822 5824 5827 5830-5831

5833 5839 5841-5846 5848-5849 5851 5855 5859 5862-5863 5866-5867 5869

5872-5874 5876 5878-5879 5881 5883 5886-5889 5891 5897 5901-5903 5905-5908

5911-5914 5917-5919 5921 5925-5927 5929 5931 5933-5935 5943 5945 5950 5957

5959 5963 5965-5967 5969-5970 5972-5974 5976 5981-5982 5984 5989-5990 5995

5997 6000 6003-6006 6011-6013 6015-6017 6021-6022 6024-6026 6033-6034

6038-6045 6047-6048 6050-6051 6053-6057 6060-6061 6064-6067 6069 6071-6073

6075 6079-6081 6084-6085 6087-6088 6090 6092 6095-6096 6102-6103 6105 6107

6110-6112 6114 6116-6119 6122 6124-6125 6127 6135 6139 6141 6144-6145

6149-6151 6153-6154 6156-6158 6160 6164 6166-6174 6176-6179 6183-6184 6188

6192 6196 6202 6204 6206-6207 6209-6210 6213 6215-6216 6218 6220-6221

6224-6225 6231-6232 6234 6239-6240 6242-6244 6246 6248 6250-6251 6257-6260

6262-6263 6265 6267-6270 6274 6276-6277 6280-6283 6285 6292-6293 6301 6307

6309-6310 6312 6314-6315 6317-6320 6322-6323 6325 6328-6329 6333 6335

6338-6339 6341-6342 6347-6351 6353 6355-6358 6361 6364-6365 6367-6369

6372-6373 6375-6376 6378-6380 6384 6386 6389 6391-6393 6397-6398 6403-6406

6408-6414 6416 6418 6422-6423 6428-6430 6432-6435 6437-6438 6441-6442 6444

6446-6447 6452-6454 6456-6459 6465-6469 6476-6477 6481 6484-6485 6488

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 4

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SERVICE BULLETIN

6491-6492 6494 6496-6498 6500-6503 6505 6509 6511 6514-6516 6519 6521

6524-6526 6528-6529 6536 6538 6540-6542 6545-6550 6552-6553 6561-6562

6564-6565 6567-6568 6570 6572 6577 6579 6582 6584-6585 6587-6588 6590-6592

6595-6598 6600 6603 6605-6606 6608 6615 6617 6619 6622 6626-6629 6632-6634

6636-6637 6639-6641 6644 6646 6648 6651 6653-6654 6658 6661 6664-6666

6669-6671 6674-6681 6685-6686 6689-6690 6692 6695-6699 6701-6702 6704

6707-6708 6710 6712-6719 6721-6722 6724 6726-6730 6732 6737-6739 6741-6743

6746-6747 6753-6754 6756 6759 6762 6764-6765 6767 6769 6773 6776-6777

6779-6780 6782 6784 6786-6789 6793 6797-6798 6800 6803 6805-6808 6811

6813-6815 6817 6823-6826 6830-6831 6834-6838 6843-6847 6852 6855-6856 6858

6862 6870-6874 6876-6879 6881 6884-6885 6889-6896 6899-6900 6902 6905 6911

6916 6918 6921-6927 6929

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

07P 6347 6467 6494 6529 6622 6646 6717 6811

11S 4211

15T 0764 1494 2910 3164 3261 6727

16T 4024 4679

17R 5768

17S 3333

17W 3046

27V 3826

31P 0229

31V 0293 0420 0436 0605 0885 1048

32Q 1283

35T 5040

35U 0088 0199 0240 0241 0264

36R 1305

40S 1973

41S 0630

43S 4650

47P 0619

52T 1599

59Z 1556

61W 0112

69X 0212 0219 0300 0328 0588

73W 0087

74T 2165 4228 4768

76W 0140 0157

79W 3751

80X 2748

83Q 1299

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 5

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SERVICE BULLETIN

OPERATOR MSN

83V 0938

85T 0190 0234

85U 5792

86Z 0409 0419 1706 1750

89T 3356

90Q 0594

91X 2837

95W 2949 4199

98W 0434 0515 0516 0524

AAF 0639 2870 3136 3242 3289 3852 4268 4589 4675 6012

AAL 5327 5678 5698 5704 5745 5753 5761 5781 5786 5788 5789 5798

5810 5827 5842 6040 6085 6150 6154 6263 6277 6310 6349 6384

6393 6429 6437 6456 6491 6552 6595 6644

AAW 3224 3236 3615 3657 4004 4521 5414 5448

AAY 1229 1255 1262 1288 1292 1318 1347 1530 1540 2224 2265 2271

2319 2387

ABQ 1467 3974 5891 5943

ABY 2764 3802 3840 3925 4061 4243 4310 4468 4524 4806 4848 4890

4958 5017 5206 5276 5307 5423 5452 5502 5576 5718 5772 5889

5903 5984 6000 6054 6080 6166 6176 6234 6293 6365 6430 6444

6481 6553 6665 6737

ACA 0059 0068 0073 0084 0122 0126 0127 0141 0149 0150 0154 0159

0174 0175 0183 0210 0231 0232 0233 0242 0248 0253 0254 0255

0265 0277 0284 0290 0309 0324 0330 0341 0378 0403 0404 0546

0572 0634 0656 0670 0672 0682 0688 0691 0693 0695 0697 0711

0719 0721 0728 0732 0736 0740 0742 0752 0757 0769 0773 0779

0785 0800 0813 0817 0829 0831 0840 0845 1562 1577 1602 1611

1623 1632 1638 1673 1719 1726 1742 1748 1772 1783 1787 1811

1853 1864 1874 1940 1975 2018 2145 3051

ADH 3328

AFL 2052 2069 2072 2091 2106 2116 2133 2144 2233 2330 2337 2342

2875 2903 2912 2920 2947 2957 2965 3052 3063 3157 3191 3267

3334 3373 3410 3511 3545 3574 3627 3631 3640 3644 3699 3711

3778 3786 3789 3794 3823 3835 3923 3942 3954 3998 4058 4074

4099 4103 4116 4133 4148 4160 4453 4461 4498 4500 4579 4625

4649 4656 4684 4692 4712 4835 5044 5059 5271 5421 5536 5565

5572 5578 5580 5585 5614 5720 5755 5790 5873 5881 5913 5921

5967 5970 5974 5982 5989 6017 6022 6043 6044 6060 6071 6090

AFR 0115 0214 0237 0239 0285 0287 0498 0509 0521 0529 0544 0598

0600 0608 0618 0625 0637 0777 0796 0985 0998 1000 1020 1025

1036 1133 1151 1169 1176 1190 1201 1216 1267 1271 1344 1404

1415 1444 1449 1471 1476 1502 1505 1524 1616 1622 1640 1645

1658 1677 1691 1699 1733 1859 1879 1894 1900 1924 1938 1949

2035 2059 2071 2081 2100 2109 2140 2317 2344 2350 2456 2582

2601 2686 2705 2716 2721 2750 2918 2938 2951 2961 2967 2972

3008 3009 3098 3372 3399 3401 3419 3420 3441 3470 3777 3795

3814 3825 3859 3884 3930 4063 4084 4105 4137 4139 4241 4251

4267 4295 4298 4335 4402 4601 4604 4664 4714 4747 4800 4820

4901 4908 5084 5129 5719 5802 5869

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 6

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SERVICE BULLETIN

OPERATOR MSN

AHY 0331 2487 2516 2588 2685 2788 2846 2853 2865 2991 3006 6285

AIB 0138 6879 6916 6927

AIC 2593 2624 2629 2907 3130 3146 3212 3271 3288 3300 3305 3326

3340 3344 3367 3498 3551 3557 3573 3619 3620 3687 3752 3792

3822 3874 3918 3955 3970 4002 4009 4020 4029 4052 4078 4089

4096 4121 4138 4155 4164 4201 4212 4236 4237 4280 6446

AIJ 0707 1132 1162 1179 1244 1259 1308 1322 1780 2048 2227 2539

3021 3123 3149 3160 3286 3304 3312 3374 3508 3514 3667 3690

4235 4304 4411 4730 4733 4924 4933 5163 5221 5358 5372 5653

5665 5867 5878 5933

AJD 0879

ALK 2584 4694 4869 4915 5086

AMC 2113 2122 2189 2291 2332 2382 2665 2768 3056 3068

ANA 0167 0383 0413 0482 0501 0507 0531 0534 0549 0554 0658 0669

0685

ANR 0445 0671 0726

AOJ 4503

APJ 4887 4936 5015 5166 5304 5384 5440 5540 5640 5724 5874 6004

6107 6335 6640 6674 6824

ART 0142 0244 0333 0359 0533 0662 0888 0936 1873

AUA 0552 0570 0581 0768 0776 0797 0920 0935 1137 1150 1189 1385

1387 1458 1478 1504 1553 1678 1735 1931 1937 2009 2131 2174

2262 2416 2494 2547 2652

AVA 1612 1634 2066 2328 2333 2358 2367 2377 2394 2523 2544 2552

2575 2662 3408 3467 3518 3647 3664 3691 3961 3980 3988 3992

4001 4011 4026 4046 4051 4100 4167 4175 4200 4281 4284 4345

4381 4487 4567 4599 4763 4789 4821 4862 4939 5057 5119 5195

5243 5360 5398 5454 5477 5622 5632 6153 6167 6174 6209 6411

6692 6739 6746 6862

AWM 0765

AXM 1286 2425 2612 2633 2656 2683 2699 2760 2816 2826 2842 2881

2885 2926 2944 2956 2989 3000 3018 3064 3117 3140 3154 3173

3182 3194 3201 3223 3232 3277 3291 3299 3327 3338 3353 3370

3394 3404 3427 3448 3477 3486 3489 3505 3521 3536 3549 3568

3576 3582 3610 3628 3648 3679 3701 3715 3729 3765 3776 3813

3875 3963 3997 4019 4035 4070 4079 4088 4098 4126 4147 4263

4278 4293 4302 4333 4346 4361 4367 4386 4390 4404 4426 4458

4462 4477 4486 4557 4571 4582 4793 4797 4807 4882 4889 4917

4964 4969 4979 4980 4989 5098 5137 5149 5153 5165 5200 5215

5272 5283 5325 5344 5347 5353 5359 5397 5420 5428 5430 5431

5468 5505 5547 5593 5619 5627 5657 5703 5706 5762 5812 5824

5839 5846 5851 5863 5866 5888 5897 5905 5908 5914 5918 5959

6015 6034 6048 6064 6075 6084 6088 6096 6105 6145 6149 6158

6170 6178 6204 6215 6240 6262 6405 6428 6492 6597 6619 6666

6676 6702

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 7

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SERVICE BULLETIN

OPERATOR MSN

AZA 0477 0488 0495 0513 0514 0526 0532 0576 0583 0586 0593 0599

0819 0848 0940 0951 0959 1138 1168 1217 1220 1448 1457 1473

1480 1489 1722 1740 1745 1770 1779 2033 2057 2074 2083 2086

2101 2127 2869 2932 3076 3079 3080 3115 3138 3161 3213 3295

3343 3362 3563 3598 3609 3643 3666 3695 3732 3815 3831 3846

3885 3906 3921 3956 3976 3978 4075 4108 4119 4143 4152 4195

4249 4520 4523 4536 4759 4764 4859 4875 4910 5018 5130 5294

5383 5424

B2V 0185

BAW 4007 4039

BEC 3199 5538

BEL 0644 1086 1102 1160 1336 1388 1441 1493 1797 1838 1885 1963

2196 2230 2392 2400 2700 2763 2810 2925 3255 3790 3895 4275

BER 1629 1717 1769 1775 1852 1889 1961 1966 1988 1994 2003 2005

2619 3055 3093 3121 3178 3202 3412 3415 3464 3482 3502 3515

3516 3532 3689 3708 3728 3749 3865 3945 4013 4101 4161 4269

4291 4329 4334 4433 4510 4565 4606 4728 4743 4988 5038 5126

5133 5191 5246 5522 6168 6432 6454 6501 6629 6639 6719 6831

6856 6877 6892 6902

BGF 3188

BGH 1087 3139

BHP 2968 3245 3422 3604 4033 4187 4294 4631

BIE 0519 0827 0891

BJN 3617 4956

BSX 0648 0650

BTK 6164 6280 6309 6356 6361 6372 6505 6628 6695 6697 6722 6782

6823

BTN 1541 1551

C2C 5088 5907

C8J 5545

C9G 1747 1846

CAA 0279

CBJ 2557 2561 2611 2644 2733 2849 2891 2985 3285 5008 5072 5114

5216 5331 5471 5630 5656 5722 5848 5997 6041 6206 6570 6664

6730 6759 6769

CCA 0876 0921 1296 2237 2269 2285 2293 2298 2499 2508 2525 2532

2545 2551 2805 2819 2839 2847 2890 3215 3221 3226 3250 3307

3329 3337 3461 3506 3523 3601 3623 3653 3655 3665 3678 3722

3725 3766 3806 3940 3973 4022 4031 4062 4091 4131 4180 4221

4283 4318 4377 4472 4494 4538 4803 4829 4895 4900 4963 4985

5014 5032 5174 5386 5419 5435 5568 5573 5664 5690 5743 5771

6013 6169 6196 6239 6251 6283 6319 6466 6514 6567 6579 6603

6641 6699 6743

CCM 3882 3952 5887 5906

CDC 6026 6055 6065 6157 6600 6648 6671 6679 6714 6764 6789 6805

6847 6921

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 8

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SERVICE BULLETIN

OPERATOR MSN

CEB 2556 2586 2625 2638 2786 2790 2821 2831 2852 2876 2994 3048

3272 3762 3767 4447 4508 4537 4574 4852 4861 4870 4927 4993

5045 5067 5250 5320 5381 5442 5498 5669 5687 5917 5934 6021

6051 6317 6325 6418 6441 6741 6777 6925 6929

CEF 2801 3085

CES 0665 0754 0838 0854 0897 0909 0925 0939 0967 0984 0986 1028

1030 1041 1070 1072 1093 1108 1285 1303 1312 1316 1330 1345

1357 1361 1377 1386 1532 1542 1601 1639 1906 1911 1964 1981

2022 2034 2036 2049 2056 2068 2219 2221 2235 2239 2244 2309

2315 2437 2451 2478 2493 2498 2543 2549 2562 2591 2606 2627

2693 2757 2825 2882 2895 3168 3170 3186 3197 3233 3247 3249

3262 3471 3559 3593 3611 3612 3639 3682 4627 4659 4685 4702

4709 4711 4718 4722 4723 4729 4748 4765 4769 4776 4799 4831

4844 4857 4877 4886 4903 4938 4946 4967 4987 5047 5048 5063

5136 5273 5330 5338 5380 5412 5527 5668 5691 5710 5726 5735

5759 5886 5973 6111 6116 6127 6144 6151 6160 6213 6250 6258

6260 6269 6274 6307 6323 6355 6368 6373 6379 6453 6469 6519

6582 6661 6762 6814 6836 6872 6890

CFG 5969 6053 6376 6459 6590 6615

CHB 5626 5679 5740 5912

CIB 0774 0809 0884 0894 0905 0957 0971 1381 1402 1416 1437 1607

1968

CQH 0978 1920 2939 3014 3023 3747 3819 4072 4093 4168 4244 4331

4366 4373 4375 4499 4586 4738 4750 4760 4809 4816 4909 4978

4983 5022 5051 5108 5378 5403 5434 5446 5466 5562 5778 5816

5911 6073 6117 6216 6218 6220 6231 6318 6329 6358 6403 6410

6452 6497 6524 6591 6765 6786 6815 6826 6846 6858 6870 6874

6881 6900 6924

CQN 3903

CRK 5147 5189 5416 5514 5544 6003 6246 6442 6776

CSA 2719 2758 2789 3031 3043 3060 3094 3097 3406 3436 3452 3660

3892 4258 4713

CSC 6339 6367 6369 6386 6397 6540 6654 6677 6710 6713 6732

CSN 2354 2361 2484 2506 2511 2519 2541 2546 2554 2555 2558 2637

2708 2743 2770 2796 2824 2834 2855 2861 2877 2899 2915 2950

2960 2986 3828 3983 4038 4071 4172 4194 4205 4274 4322 4325

4338 4362 4365 4369 4396 4416 4456 4507 4550 4613 4671 4794

4808 4854 4880 4928 5693 5730 5945 5976

CSZ 2672 2684 2841 2905 2909 2935 2973 2980 3131 3132 3153 3206

3366 3383 3435 3440 3456 3528 3599 3696 3698 3756 3848 3855

3887 3898 3971 4010 4028 4159 4208 4226 4876 5082 5110 5369

5521 5550 5589 5639 5731 5766 6564 6626 6686 6708 6721 6728

6742 6911

CTN 0767 0833 1009 1029 1237 1252

CTV 3147 3148 3861 5351 5379 5394 5399 5415 5511 5541 5551 5556

5560 5571 5574 5597 5777 5830 6118 6207 6224 6322 6408

CUA 5023

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 9

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SERVICE BULLETIN

OPERATOR MSN

DAL 0118 0121 0125 0152 0153 0160 0171 0192 0197 0206 0208 0213

0262 0263 0272 0273 0281 0282 0297 0298 0306 0307 0318 0319

0329 0339 0340 0355 0358 0360 0367 0372 0380 0381 0387 0388

0399 0408 0410 0417 0418 0766 0778 0786 0801 0807 0818 0830

0832 0846 0903 0907 0911 0923 0962 0964 0981 0988 0996 1011

1037 1058 1062 1191 1230 1249 1324 1325 1346 1392 1414 1434

1453 1456 1483 1498 1501 1520 1535 1543 1549 1567 1570 1582

1633 1641 1646 1659 1662 1683 1685 1693 1709 1714 1738 1746

1752 1766 1774 1789 1796 1800 1810 1812 1815 1820 1824 1828

1833 1839 1875 1897 1923 1959 1976 1982 1990 2002 2013 2026

2039 2047 2082 2087 2092 2095 6923

DAT 0311 0395 0426 0525 0999

DCS 3243

DKH 2975 3027 3234 3268 3368 3485 3596 3605 3967 3984 4064 4102

4154 4276 4401 4429 4573 4587 4652 4833 4840 4981 5013 5070

5071 5131 5226 5329 5339 5455 5491 5674 5737 5876 6172 6221

6315 6392 6433 6435 6477 6542 6627 6637 6701 6808 6843 6855

DLH 0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110 0111

0116 0137 0172 0346 0609 0610 0616 0623 0627 0636 0641 0651

0679 0689 0694 0700 0717 0723 0729 0738 0744 0853 0860 0875

1337 1365 1367 4097 4120 4141 4153 4182 4191 4261 4289 4324

4332 4363 4398 4449 4455 4511 4796 4841 5122 5181 5203 5239

5284 5293 5425 5441 5487 5694 5741 5769 5831 5935 5972 6006

6033 6092 6141 6202 6225 6265 6301 6423 6521 6549 6577 6636

6807

DNV 1630 1805 1808 1841 2093 2179 2241 2751 3065 3179

DQA 2347 2599

DRK 2306 2346 3950 6496

EDW 0942 0947 1026 2024 2134

EIN 0926 1023 1094 1242 1394 1443 1983 2001 2191 2206 2217 2250

2256 2272 2294 2364 2374 2399 2409 2411 2432 2486 2542 2583

2635 3054 3102 3129 3169 3318 3345 3377 3501 3755 3781 3857

4572 4634 4678 4715

ETD 0350

ETJ 0325

EVA 3363 3886 5328 5354 5377 5485 5808 5849 6024 6042 6087 6179

6276 6312 6488 6545 6585 6653 6707 6747

EVE 5642

EWG 5497 5525 5557 5601 5635 5658

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 10

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SERVICE BULLETIN

OPERATOR MSN

EZY 2037 2043 2050 2053 2062 2120 2170 2181 2184 2245 2289 2300

2353 2360 2370 2385 2398 2402 2412 2427 2450 2463 2471 2477

2481 2492 2495 2503 2512 2514 2527 2528 2538 2565 2578 2605

2636 2646 2677 2681 2691 2702 2709 2715 2727 2729 2735 2742

2744 2754 2765 2769 2777 2779 2782 2795 2803 2812 2818 2827

2829 2854 2860 2866 2873 2884 2923 2946 2959 3003 3036 3041

3053 3059 3061 3082 3084 3088 3090 3118 3122 3134 3137 3176

3184 3411 3413 3426 3432 3442 3466 3537 3544 3555 3569 3571

3608 3634 3675 3683 3702 3720 3735 3742 3746 3754 3763 3774

3788 3799 3805 3808 3810 3824 3843 3844 3845 3854 3871 3888

3909 3913 3922 3946 3953 3975 3979 3991 4006 4012 4014 4034

4040 4048 4056 4069 4076 4080 4087 4125 4129 4132 4157 4179

4196 4219 4233 4234 4250 4286 4313 4327 4380 4385 4418 4425

4427 4437 4444 4451 4554 4556 4588 4591 4624 4635 4636 4640

4646 4667 4676 4680 4693 4705 4708 4717 4721 4740 4744 4749

4778 4781 4785 4787 4837 5019 5020 5046 5052 5056 5064 5104

5111 5113 5116 5138 5146 5150 5187 5201 5224 5236 5249 5289

5318 5319 5542 5592 5638 5688 5702 5739 5757 5785 5927 5981

6011 6047 6095 6177 6188 6192 6267 6353 6412 6416 6485 6502

6509 6525 6541 6546 6562 6565 6568 6572 6587 6605 6606 6633

6675 6680 6754 6788 6834 6837 6885 6918

F2I 0085 0148 0203 0220 0270 0294 0301 0391 0422 0427 0497 0724

0799 1068

FFT 1515 1579 1583 1615 1684 1759 1781 1786 1803 1806 1860 1943

1980 1997 2010 2012 2019 2030 2103 2198 2209 2236 2240 2253

2258 2260 2287 2318 2325 2406 2448 2483 2518 2695 2806 2836

2857 3205 3389 3431 4127 4204 4253 4254 4272 4307 4562 4641

4668 4688 4704 4727 4745 5526 5661 6184 6773 6793 6825 6838

6845 6891 6926

FHY 3025 4207 4658 5096

FIN 0941 0961 1073 1107 1184 1185 1241 1309 1352 1364 1405 1470

1544 1588 1712 1913 1916 1978 1989 2065 2124 2146 2154 2208

2266

FLI 2186 3905 5079

FPY 0189 0342

FRN 0647 0660

FTZ 1145 2176

G2X 0653

G4I 1157 1795 2507

G8E 0714 0716 0730 2420

GAP 0706 0745 2162 2183 3087 3187 3273 4777 4984 5007 5012 5103

5310

GCR 4600 5006 5117 5760 5799 6348

GFA 4030 4059 4083 4146 4158 4188 4218 4255 4502 4541 4780 4827

4860 4865 5171 5175

GHT 0438

GIA 6243 6270 6333 6434 6503 6596 6753

GLG 1866 1872 1882 1925 2078 2126 4379 4547

GMI 0684 0970 0995 3019 3407 3533 3560 4663 4691 5085 5843 6005

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 11

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SERVICE BULLETIN

OPERATOR MSN

GOW 3306 3597 3616 3798 3827 3900 3915 4399 4438 5016 5112 5232

5463 5552 5675 5809 5811 5990 6072

GSW 3589 3818

GWI 0117 0135 0161 0162 0200 0201 0202 0209 0216 0217 0218 0267

0268 0269 0382 0401 0646 0654 0794 1016 1077 1084 1089 1136

1147 1155 1170 1172 1209 1277 2607 2628 2632

HKE 4970 5260 5264 5266 5341

HKJ 2706 3073 4878

HRM 0517 0535 0642 0666

I2L 0371 0491 0579

IAC 6690 6715 6724 6803

IAW 5115 5290 5464

IBE 0158 0173 0176 0207 0224 0266 0274 0323 0356 1021 1027 1154

1362 1572 1655 1674 1681 1694 1716 1793 1809 1836 2115 2220

2225 2242 2264 2270 2311 2357 2365 2381 2391 2472 2488 2563

2736 2756 2889 2996 3078 3209 3320 3380 3443 3651 3744 5486

5570 5692 6244 6328

IBS 1047 1059 1067 1099 1101 1119 1125 1198 1439 1450 1516 2104

2143 2248 2807 5501 5590 5729 5815

IND 0343

IRA 0303 0312 0345 2054

ISS 0737 0749

IZG 0400 0407

JAD 0459 0537 3246

JAS 5478

JAV 0029 2061

JZR 3919 3939 4162 5033 5625 5833 6124

KAC 0181 0182 0195 2046 3957 6350 6375 6458 6476 6500 6516 6538

KAY 4470 5963

KGL 0852 1554

KKK 0675 0761 0808 0823 1124 1390 1451 1503

KNE 1942 1965 2123 2171 2182 2199 2569 2776 3218 3238 3256 3361

3396 3425 3475 3530 3787 3809 3817 3868 3889 3894 3933 4055

4735 5716

LAA 4405 4450 4490 4526 5373 5405 5494

LAN 4758 4767 4815 4839 4871 4892 4896 4921 4943 4972 5005 5097

5125 5178 5213 5229 5234 5263 5316 5324 5364 5408 5443 5453

5483 5493 5548 5554 5583 5586 5654 5666 5686 5707 5748 5764

5801 5818 5859 5929 5965 6135 6183 6364 6398 6406 6484 6698

6780 6797 6894 6899

LAO 4596 4639 5356 5396

LBT 0793 0937 1121 1175 1597 1744 2158 3480 3487 4623

LIM 0828

LJB 3985

LKE 2581 2617 2746 3240 5100 5172 5220

LLC 4203 4489

LLM 1054 2419 2439

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 12

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SERVICE BULLETIN

OPERATOR MSN

LLP 0883 0914

LWA 2878 2954

LZB 2540 2596 3028 3309 3564 3780

MAC 4539 4568 5143

MAU 1592 1936

MEA 5152 5162 5253 5746

MJF 4353

MJN 3723 4117 4795

MLD 0622

MLM 2550 3932 4622

MMA 0973 1180 1247 1791

MON 1081 1320 1413 1571 1605 1637 2142 5581 6550

MOV 2442 2446 3364 3403

MSC 2937 2966 3282 3323 3626

MYX 0566

NLY 2529 2668 2749 2867 2902 3447 3504 3661 3830 4231 4316 4368

4581 4594 4611 4648 5648

NMB 3346 3586 5366 5400

NVD 0211 0528 1005 1778

NWS 1219 1233

OAW 1886

OBS 3758

ONE 4222 4287 4336 4891 4913 4941 4942 5193 5278 5299 5754 5841

6050 6057 6103 6110 6125 6139 6173 6528 6536 6561 6598 6634

6651 6689 6712 6800 6806 6813 6871 6876 6896

PAL 3310 3455 3553 3579 3652 3731 5081 5140 5315 5371

PGT 5879 5902 5950 5995 6465

PIA 2155 2212 2274

PKZ 6069

PTI 1263

QAF 3994

QDA 6061 6102 6259 6413 6547 6608 6681 6784 6893

R1T 1908 6112

RBG 3152

RCT 0466 1017

RFJ 0814

RJD 1618 5277

ROT 2931 2955 3220 3225

ROU 6844 6873 6884 6905

RYW 0569

RZO 0795 2011 2390 3891

SBI 1071 1078 1090 1091 1126 1129 1131 1149 1164 1167 1819 1870

2028 2064 2076 2279 2369 2373 2464 2474 2618 2623 2641 2726

3070 3446 3473 3490 3494 3866 3880 4032 4150 5001 5026 5031

5106 5134 5167 5559 5607 6066 6171

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 13

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SERVICE BULLETIN

OPERATOR MSN

SDM 0649 1130 1200 1379 1488 1560 1578 1654 1657 1679 1743 1753

1761 1767 1851 1863 1876 1890 2151 2163 2465 2497 2879 2913

2930 2964 3044

SFJ 4555 4720 5102 5393 5512 5652 5773 5862 5931

SFW 0734 0994 1018

SHU 2222 2243 3108 3281 3298 3336 3838

SKU 2119 2129 2214 2249 2251 2283 2378 2380 2436 2460 2548 3171

3331

SMX 2995

SND 1999

SNX 0289

SOL 0302

SUD 3040

SVA 4015 4057 4081 4090 4092 4104 4115 4122 4135 4273 4314 4337

4349 4357 4364 4376 4391 4392 4393 4394 4397 4408 4414 4419

4432 4442 4454 4467 4484 4501 4517 4519 4542 4564 4577 4590

4811 4823 4838 4925 4955 4962 5009 5065 5223 5285 5314 5447

5509 5549

SVR 0735 0775 0815 0841 0991 1012 1063 1152 1484 1603 1720 1751

1777 1884 1901 1905 2117 2166 2175 2187 2278 2327 2349 2707

2998 3099 3107 3189 3385 3388 3433 3472 3834

SVW 2592 2921 3100 3133 3542 3856 5445

SWM 0421

SWR 0520 0522 0541 0545 0553 0559 0562 0574 0577 0578 0585 0596

0603 0612 0621 0635 0643 0664 0673 0681 0701 0703 0713 0727

0782 0987 1144 1762 1951 4534 4618 4673 5037 5069 5518 5567

SYA 3853 3872

TAE 0657 0946 0949

TAI 1598 1625 5238 5333 6511 6617 6767

TAM 1692 2924 3002 3035 3047 3058 3111 3180 3211 3266 3278 3284

3313 3325 3391 3540 3565 3594 3630 3658 3662 3727 3733 3750

3908 3972 4320 4441 4446 4465 4544 4734 4756 4953 4974 5066

5101 5107 5109 5184 5209 5222 5240 5342 5591 5621 5643 5749

5752 5845 5883 6409 6414 6592 6632 6658 6670 6685 6718 6729

6798 6895

TAP 0629 0750 0755 0763 0790 0821 0837 0870 0906 0917 0933 0945

0960 0979 0982 1034 1100 1106 1120 1127 1165 1181 1206 1231

1307 1399 1667 1668 1713 1718 1756 1765 1799 1816 2178 2792

2822 3769 3883 4021 4095 4106 4145

TAR 0119 0123 0124 0205 0370 0390 0402 0511 0869 0880 0958 0975

1187 1479 1700 3096 4344 4689 5204 5474 5610 6338

TBA 4766 4801 4846 5157 5256 5451 5529 5563 5855 6380 6391 6404

6588 6716

TBJ 1485

TCW 1929 2114

TCX 0677 1006 1238 1250 1887 2060 5603 5872 6038 6056 6114 6122

6515 6526 6548

THY 1002 3896 3931 3949

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 14

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SERVICE BULLETIN

OPERATOR MSN

TJS 3513 3632 4169

TSO 6678 6726 6756 6817

TVS 2180 4699

TXP 0607 0611 0617

UAE 4822

UEA 2654 2696 2762 2774 2820 2835 3024 3706 4347 5003 5252 5957

6248 6281 6292 6357 6830 6922

UJX 1213

UKN 3260

UNA 4732

USA 0844 0861 0863 0868 0890 0896 0904 0922 0929 0972 0997 1019

1033 1038 1040 1046 1051 1052 1055 1061 1065 1069 1095 1097

1109 1112 1114 1122 1134 1135 1141 1148 1182 1203 1205 1224

1245 1254 1264 1265 1268 1269 1275 1287 1289 1294 1297 1298

1301 1310 1311 1313 1314 1315 1317 1319 1326 1328 1331 1340

1342 1348 1354 1358 1360 1369 1371 1378 1382 1389 1391 1393

1403 1412 1417 1425 1431 1436 1442 1447 1455 1462 1465 1472

1481 1492 1496 1499 1517 1519 1521 1525 1531 1536 1539 1651

1666 1701 1704 1724 3584 3629 3633 3879 3928 4086 4149 4202

4242 5444 5475 5504 5513 5588 5594 5644 5659 5684 5696

UTA 5681 5733 5779 5919 5966 6016 6067 6119 6156 6268

UZB 4371 4395 4417 4485 4492 4528 4651 4724 4770 4952

VJC 2712 2745 3646 3739 3791 4049 4190 4193 4415 4475 4504 4512

4907 5295 5742 5822 6025 6242 6341 6378 6457 6498 6584 6696

6738 6779 6852 6878

VKG 1881 1921 1932 1954 1960 1972 6314 6342 6351 6389 6438 6468

VLE 1226

VLG 0992 1171 1208 1210 1221 1372 1396 1430 1461 1550 1736 2207

2388 2407 2620 2658 2678 2761 2785 2794 2798 2843 2897 2962

2988 3083 3095 3109 3145 3151 3174 3203 3237 3293 3321 3376

3400 3444 3476 3492 3529 3700 3704 3833 3907 3995 4128 4463

4478 4661 4674 4681 4742 4849 4855 4937 5533 5587 5616 5673

5925 6039 6045 6079 6081

VNL 5844 5901 5926 6257 6282 6320 6422 6447

VRD 2616 2674 2740 2773 2778 2800 2811 2830 2851 2993 3016 3037

3101 3135 3155 3181 3204 3230 3324 3347 3349 3359 3398 3417

3445 3460 3465 3503 3656 3670 3684 3686 4448 4480 4558 4559

4610 4616 4655 4805 4814 4851 4867 4894 4948 4959 4991 4999

5004 5034 5058 5179 5515 6669 6704 6787 6835 6889

VRE 1429 2213 2228

VVC 1306 1370 1454 1564 1686 1725 1757 1867

WHT 0548 2440 2675

WOW 6210 6232

WRC 0235 0645 0781

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 15

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SERVICE BULLETIN

(4) Configuration by MSN

MSN CONFIGURATION

0029 0059 0068 0069 0070 0071 0072 0073 0078 0083 0084

0085 0086 0087 0088 0093 0094 0104 0110 0111 0112 0115

0116 0117 0118 0119 0121 0122 0123 0124 0125 0126 0127

0135 0137 0138 0140 0141 0142 0148 0149 0150 0152 0153

0154 0157 0158 0159 0160 0161 0162 0167 0171 0172 0173

0174 0175 0176 0181 0182 0183 0185 0189 0190 0192 0195

0197 0199 0200 0201 0202 0203 0205 0206 0207 0208 0209

0210 0211 0212 0213 0214 0216 0217 0218 0219 0220 0224

0229 0231 0232 0233 0234 0235 0237 0239 0240 0241 0242

0244 0248 0253 0254 0255 0262 0263 0264 0265 0266 0267

0268 0269 0270 0272 0273 0274 0277 0279 0281 0282 0284

0285 0287 0289 0290 0293 0294 0297 0298 0300 0301 0302

0303 0306 0307 0309 0311 0312 0318 0319 0323 0324 0325

0328 0329 0330 0331 0333 0339 0340 0341 0342 0343 0345

0346 0350 0355 0356 0358 0359 0360 0367 0370 0371 0372

0378 0380 0381 0382 0383 0387 0388 0390 0391 0395 0399

0400 0401 0402 0403 0404 0407 0408 0409 0410 0413 0417

0418 0419 0420 0421 0422 0426 0427 0436 0438 0445 0459

0466 0482 0491 0497 0501 0507 0511 0525 0528 0531 0534

0537 0546 0549 0554 0569 0572 0579 0598 0600 0608 0609

0610 0616 0618 0622 0623 0625 0627 0634 0636 0637 0639

0641 0644 0645 0647 0649 0651 0656 0658 0660 0662 0669

0670 0671 0672 0679 0682 0685 0688 0689 0691 0693 0694

0695 0697 0700 0711 0717 0719 0721 0723 0726 0728 0729

0732 0736 0738 0740 0742 0744 0752 0757 0766 0769 0773

0774 0778 0779 0785 0786 0793 0795 0800 0801 0807 0809

0813 0814 0817 0818 0829 0830 0831 0832 0840 0845 0846

0853 0860 0869 0875 0880 0884 0894 0903 0905 0907 0911

0923 0937 0957 0958 0962 0964 0971 0975 0981 0988 0996

1011 1037 1058 1062 1071 1078 1090 1091 1126 1129 1131

1149 1164 1167 1187 1191 1230 1249 1324 1325 1337 1346

1365 1367 1381 1392 1402 1414 1416 1434 1437 1453 1456

1479 1483 1498 1501 1520 1535 1543 1549 1567 1570 1582

1633 1641 1646 1659 1662 1683 1685 1693 1700 1709 1714

1738 1746 1752 1766 1774 1789 1796 1800 1810 1812 1815

1819 1820 1824 1828 1833 1839 1870 1875 1897 1923 1959

1973 1976 1982 1990 2002 2013 2026 2028 2039 2046 2047

2054 2061 2082 2087 2092 2095 2369 2373 2464 2474 2618

2641

001

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 16

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SERVICE BULLETIN

MSN CONFIGURATION

0434 0477 0488 0495 0498 0509 0513 0514 0515 0516 0517

0519 0520 0521 0522 0524 0526 0529 0532 0533 0535 0541

0544 0545 0548 0552 0553 0559 0562 0566 0570 0574 0576

0577 0578 0581 0583 0585 0586 0588 0593 0594 0596 0599

0603 0605 0607 0611 0612 0617 0619 0621 0629 0630 0635

0642 0643 0646 0648 0650 0653 0654 0657 0664 0665 0666

0673 0675 0677 0681 0684 0701 0703 0706 0707 0713 0714

0716 0724 0727 0730 0734 0735 0737 0745 0749 0750 0754

0755 0761 0763 0764 0765 0767 0768 0775 0776 0777 0781

0782 0790 0794 0796 0797 0799 0808 0815 0819 0821 0823

0827 0828 0833 0837 0838 0841 0844 0848 0852 0854 0861

0863 0868 0870 0876 0879 0883 0885 0888 0890 0891 0896

0897 0904 0906 0909 0914 0917 0920 0921 0922 0925 0926

0929 0933 0935 0936 0938 0939 0940 0941 0942 0945 0946

0947 0949 0951 0959 0960 0961 0967 0970 0972 0973 0978

0979 0982 0984 0985 0986 0987 0991 0992 0994 0995 0997

0998 0999 1000 1002 1005 1006 1009 1012 1016 1017 1018

1019 1020 1021 1023 1025 1026 1027 1028 1029 1030 1033

1034 1036 1038 1040 1041 1046 1047 1048 1051 1052 1054

1055 1059 1061 1063 1065 1067 1068 1069 1070 1072 1073

1077 1081 1084 1086 1087 1089 1093 1094 1095 1097 1099

1100 1101 1102 1106 1107 1108 1109 1112 1114 1119 1120

1121 1122 1124 1125 1127 1130 1132 1133 1134 1135 1136

1137 1138 1141 1144 1145 1147 1148 1150 1151 1152 1154

1155 1157 1160 1162 1165 1168 1169 1170 1171 1172 1175

1176 1179 1180 1181 1182 1184 1185 1189 1190 1198 1200

1201 1203 1205 1206 1208 1209 1210 1213 1216 1217 1219

1220 1221 1224 1226 1229 1231 1233 1237 1238 1241 1242

1244 1245 1247 1250 1252 1254 1255 1259 1262 1263 1264

1265 1267 1268 1269 1271 1275 1277 1283 1285 1286 1287

1288 1289 1292 1294 1296 1297 1298 1299 1301 1303 1305

1306 1307 1308 1309 1310 1311 1312 1313 1314 1315 1316

1317 1318 1319 1320 1322 1326 1328 1330 1331 1336 1340

1342 1344 1345 1347 1348 1352 1354 1357 1358 1360 1361

1362 1364 1369 1370 1371 1372 1377 1378 1379 1382 1385

1386 1387 1388 1389 1390 1391 1393 1394 1396 1399 1403

1404 1405 1412 1413 1415 1417 1425 1429 1430 1431 1436

1439 1441 1442 1443 1444 1447 1448 1449 1450 1451 1454

1455 1457 1458 1461 1462 1465 1467 1470 1471 1472 1473

1476 1478 1480 1481 1484 1485 1488 1489 1492 1493 1494

1496 1499 1502 1503 1504 1505 1515 1516 1517 1519 1521

1524 1525 1530 1531 1532 1536 1539 1540 1541 1542 1544

1550 1551 1553 1554 1556 1560 1562 1564 1571 1572 1577

1578 1579 1583 1588 1592 1597 1598 1599 1601 1602 1603

1605 1607 1611 1612 1615 1616 1618 1622 1623 1625 1629

1630 1632 1634 1637 1638 1639 1640 1645 1651 1654 1655

1657 1658 1666 1667 1668 1673 1674 1677 1678 1679 1681

1684 1686 1691 1692 1694 1699 1701 1704 1706 1712 1713

1716 1717 1718 1719 1720 1722 1724 1725 1726 1733 1735

002

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SERVICE BULLETIN

MSN CONFIGURATION

1736 1740 1742 1743 1744 1745 1747 1748 1750 1751 1753

1756 1757 1759 1761 1762 1765 1767 1769 1770 1772 1775

1777 1778 1779 1780 1781 1783 1786 1787 1791 1793 1795

1797 1799 1803 1805 1806 1808 1809 1811 1816 1836 1838

1841 1846 1851 1852 1853 1859 1860 1863 1864 1866 1867

1872 1873 1874 1876 1879 1881 1882 1884 1885 1886 1887

1889 1890 1894 1900 1901 1905 1906 1908 1911 1913 1916

1920 1921 1924 1925 1929 1931 1932 1936 1937 1938 1940

1942 1943 1949 1951 1954 1960 1961 1963 1964 1965 1966

1968 1972 1975 1978 1980 1981 1983 1988 1989 1994 1997

1999 2001 2003 2005 2009 2010 2011 2012 2018 2019 2022

2024 2030 2033 2034 2035 2036 2037 2043 2048 2049 2050

2052 2053 2056 2057 2059 2060 2062 2064 2065 2066 2068

2069 2071 2072 2074 2076 2078 2081 2083 2086 2091 2093

2100 2101 2103 2104 2106 2109 2113 2114 2115 2116 2117

2119 2120 2122 2123 2124 2126 2127 2129 2131 2133 2134

2140 2142 2143 2144 2145 2146 2151 2154 2155 2158 2162

2163 2165 2166 2170 2171 2174 2175 2176 2178 2179 2180

2181 2182 2183 2184 2186 2187 2189 2191 2196 2198 2199

2206 2207 2208 2209 2212 2213 2214 2217 2219 2220 2221

2222 2224 2225 2227 2228 2230 2233 2235 2236 2237 2239

2240 2241 2242 2243 2244 2245 2248 2249 2250 2251 2253

2256 2258 2260 2262 2264 2265 2266 2269 2270 2271 2272

2274 2278 2279 2283 2285 2287 2289 2291 2293 2294 2298

2300 2306 2309 2311 2315 2317 2318 2319 2325 2327 2328

2330 2332 2333 2337 2342 2344 2346 2347 2349 2350 2353

2354 2357 2358 2360 2361 2364 2365 2367 2370 2374 2377

2378 2380 2381 2382 2385 2387 2388 2390 2391 2392 2394

2398 2399 2400 2402 2406 2407 2409 2411 2412 2416 2419

2420 2425 2427 2432 2436 2437 2439 2440 2442 2446 2448

2450 2451 2456 2460 2463 2465 2471 2472 2477 2478 2481

2483 2484 2486 2487 2488 2492 2493 2494 2495 2497 2498

2499 2503 2506 2507 2508 2511 2512 2514 2516 2518 2519

2523 2525 2527 2528 2529 2532 2538 2539 2540 2541 2542

2543 2544 2545 2546 2547 2548 2549 2550 2551 2552 2554

2555 2556 2557 2558 2561 2562 2563 2565 2569 2575 2578

2581 2582 2583 2584 2586 2588 2591 2592 2593 2596 2599

2601 2605 2606 2607 2611 2612 2616 2617 2619 2620 2623

2624 2625 2627 2628 2629 2632 2633 2635 2636 2637 2638

2644 2646 2652 2654 2656 2658 2662 2665 2668 2672 2674

2675 2677 2678 2681 2683 2684 2685 2686 2691 2693 2695

2696 2699 2700 2702 2705 2706 2707 2708 2709 2712 2715

2716 2719 2721 2726 2727 2729 2733 2735 2736 2740 2742

2743 2744 2745 2746 2748 2749 2750 2751 2754 2756 2757

2758 2760 2761 2762 2763 2764 2765 2768 2769 2770 2773

2774 2776 2777 2778 2779 2782 2785 2786 2788 2789 2790

2792 2794 2795 2796 2798 2800 2801 2803 2805 2806 2807

2810 2811 2812 2816 2818 2819 2820 2821 2822 2824 2825

2826 2827 2829 2830 2831 2834 2835 2836 2837 2839 2841

2842 2843 2846 2847 2849 2851 2852 2853 2854 2855 2857

2860 2861 2865 2866 2867 2869 2870 2873 2875 2876 2877

002

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SERVICE BULLETIN

MSN CONFIGURATION

2878 2879 2881 2882 2884 2885 2889 2890 2891 2895 2897

2899 2902 2903 2905 2907 2909 2910 2912 2913 2915 2918

2920 2921 2923 2924 2925 2926 2930 2931 2932 2935 2937

2938 2939 2944 2946 2947 2949 2950 2951 2954 2955 2956

2957 2959 2960 2961 2962 2964 2965 2966 2967 2968 2972

2973 2975 2980 2985 2986 2988 2989 2991 2993 2994 2995

2996 2998 3000 3002 3003 3006 3008 3009 3014 3016 3018

3019 3021 3023 3024 3025 3027 3028 3031 3035 3036 3037

3040 3041 3043 3044 3046 3047 3048 3051 3052 3053 3054

3055 3056 3058 3059 3060 3061 3063 3064 3065 3068 3070

3073 3076 3078 3079 3080 3082 3083 3084 3085 3087 3088

3090 3093 3094 3095 3096 3097 3098 3099 3100 3101 3102

3107 3108 3109 3111 3115 3117 3118 3121 3122 3123 3129

3130 3131 3132 3133 3134 3135 3136 3137 3138 3139 3140

3145 3146 3147 3148 3149 3151 3152 3153 3154 3155 3157

3160 3161 3164 3168 3169 3170 3171 3173 3174 3176 3178

3179 3180 3181 3182 3184 3186 3187 3188 3189 3191 3194

3197 3199 3201 3202 3203 3204 3205 3206 3209 3211 3212

3213 3215 3218 3220 3221 3223 3224 3225 3226 3230 3232

3233 3234 3236 3237 3238 3240 3242 3243 3245 3246 3247

3249 3250 3255 3256 3260 3261 3262 3266 3267 3268 3271

3272 3273 3277 3278 3281 3282 3284 3285 3286 3288 3289

3291 3293 3295 3298 3299 3300 3304 3305 3306 3307 3309

3310 3312 3313 3318 3320 3321 3323 3324 3325 3326 3327

3328 3329 3331 3333 3334 3336 3337 3338 3340 3343 3344

3345 3346 3347 3349 3353 3356 3359 3361 3362 3363 3364

3366 3367 3368 3370 3372 3373 3374 3376 3377 3380 3383

3385 3388 3389 3391 3394 3396 3398 3399 3400 3401 3403

3404 3406 3407 3408 3410 3411 3412 3413 3415 3417 3419

3420 3422 3425 3426 3427 3431 3432 3433 3435 3436 3440

3441 3442 3443 3444 3445 3446 3447 3448 3452 3455 3456

3460 3461 3464 3465 3466 3467 3470 3471 3472 3473 3475

3476 3477 3480 3482 3485 3486 3487 3489 3490 3492 3494

3498 3501 3502 3503 3504 3505 3506 3508 3511 3513 3514

3515 3516 3518 3521 3523 3528 3529 3530 3532 3533 3536

3537 3540 3542 3544 3545 3549 3551 3553 3555 3557 3559

3560 3563 3564 3565 3568 3569 3571 3573 3574 3576 3579

3582 3584 3586 3589 3593 3594 3596 3597 3598 3599 3601

3604 3605 3608 3609 3610 3611 3612 3615 3616 3617 3619

3620 3623 3626 3627 3628 3629 3630 3631 3632 3633 3634

3639 3640 3643 3644 3646 3647 3648 3651 3652 3653 3655

3656 3657 3658 3660 3661 3662 3664 3665 3666 3667 3670

3675 3678 3679 3682 3683 3684 3686 3687 3689 3690 3691

3695 3696 3698 3699 3700 3701 3702 3704 3706 3708 3711

3715 3720 3722 3723 3725 3727 3728 3729 3731 3732 3733

3735 3739 3742 3744 3746 3747 3749 3750 3751 3752 3754

3755 3756 3758 3762 3763 3765 3766 3767 3769 3774 3776

3777 3778 3780 3781 3786 3787 3788 3789 3790 3791 3792

3794 3795 3798 3799 3802 3805 3806 3808 3809 3810 3813

3814 3815 3817 3818 3819 3822 3823 3824 3825 3826 3827

3828 3830 3831 3833 3834 3835 3838 3840 3843 3844 3845

002

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REVISION No.: 01 - Apr 07/15 Page: 19

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@A318/A319/A320/A321

SERVICE BULLETIN

MSN CONFIGURATION

3846 3848 3852 3853 3854 3855 3856 3857 3859 3861 3865

3866 3868 3871 3872 3874 3875 3879 3880 3882 3883 3884

3885 3886 3887 3888 3889 3891 3892 3894 3895 3896 3898

3900 3903 3905 3906 3907 3908 3909 3913 3915 3918 3919

3921 3922 3923 3925 3928 3930 3931 3932 3933 3939 3940

3942 3945 3946 3949 3950 3952 3953 3954 3955 3956 3957

3961 3963 3967 3970 3971 3972 3973 3974 3975 3976 3978

3979 3980 3983 3984 3985 3988 3991 3992 3994 3995 3997

3998 4001 4002 4004 4006 4007 4009 4010 4011 4012 4013

4014 4015 4019 4020 4021 4022 4024 4026 4028 4029 4030

4031 4032 4033 4034 4035 4038 4039 4040 4046 4048 4049

4051 4052 4055 4056 4057 4058 4059 4061 4062 4063 4064

4069 4070 4071 4072 4074 4075 4076 4078 4079 4080 4081

4083 4084 4086 4087 4088 4089 4090 4091 4092 4093 4095

4096 4097 4098 4099 4100 4101 4102 4103 4104 4105 4106

4108 4115 4116 4117 4119 4120 4121 4122 4125 4126 4127

4128 4129 4131 4132 4133 4135 4137 4138 4139 4141 4143

4145 4146 4147 4148 4149 4150 4152 4153 4154 4155 4157

4158 4159 4160 4161 4162 4164 4167 4168 4169 4172 4175

4179 4180 4182 4187 4188 4190 4191 4193 4194 4195 4196

4199 4200 4201 4202 4203 4204 4205 4207 4208 4211 4212

4218 4219 4221 4222 4226 4228 4231 4233 4234 4235 4236

4237 4241 4242 4243 4244 4249 4250 4251 4253 4254 4255

4258 4261 4263 4267 4268 4269 4272 4273 4274 4275 4276

4278 4280 4281 4283 4284 4286 4287 4289 4291 4293 4294

4295 4298 4302 4304 4307 4310 4313 4314 4316 4318 4320

4322 4324 4325 4327 4329 4331 4332 4333 4334 4335 4336

4337 4338 4344 4345 4346 4347 4349 4353 4357 4361 4362

4363 4364 4365 4366 4367 4368 4369 4371 4373 4375 4376

4377 4379 4380 4381 4385 4386 4390 4391 4392 4393 4394

4395 4396 4397 4398 4399 4401 4402 4404 4405 4408 4411

4414 4415 4416 4417 4418 4419 4425 4426 4427 4429 4432

4433 4437 4438 4441 4442 4444 4446 4447 4448 4449 4450

4451 4453 4454 4455 4456 4458 4461 4462 4463 4465 4467

4468 4470 4472 4475 4477 4478 4480 4484 4485 4486 4487

4489 4490 4492 4494 4498 4499 4500 4501 4502 4503 4504

4507 4508 4510 4511 4512 4517 4519 4520 4521 4523 4524

4526 4528 4534 4536 4537 4538 4539 4541 4542 4544 4547

4550 4554 4555 4556 4557 4558 4559 4562 4564 4565 4567

4568 4571 4572 4573 4574 4577 4579 4581 4582 4586 4587

4588 4589 4590 4591 4594 4596 4599 4600 4601 4604 4606

4610 4611 4613 4616 4618 4622 4623 4624 4625 4627 4631

4634 4635 4636 4639 4640 4641 4646 4648 4649 4650 4651

4652 4655 4656 4658 4659 4661 4663 4664 4667 4668 4671

4673 4674 4675 4676 4678 4679 4680 4681 4684 4685 4688

4689 4691 4692 4693 4694 4699 4702 4704 4705 4708 4709

4711 4712 4713 4714 4715 4717 4718 4720 4721 4722 4723

4724 4727 4728 4729 4730 4732 4733 4734 4735 4738 4740

4742 4743 4744 4745 4747 4748 4749 4750 4756 4758 4759

4760 4763 4764 4765 4766 4767 4768 4769 4770 4776 4777

4778 4780 4781 4785 4787 4789 4793 4794 4795 4796 4797

002

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REVISION No.: 01 - Apr 07/15 Page: 20

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SERVICE BULLETIN

MSN CONFIGURATION

4799 4800 4801 4803 4805 4806 4807 4808 4809 4811 4814

4815 4816 4820 4821 4822 4823 4827 4829 4831 4833 4835

4837 4838 4839 4840 4841 4844 4846 4848 4849 4851 4852

4854 4855 4857 4859 4860 4861 4862 4865 4867 4869 4870

4871 4875 4876 4877 4878 4880 4882 4886 4887 4889 4890

4891 4892 4894 4895 4896 4900 4901 4903 4907 4908 4909

4910 4913 4915 4917 4921 4924 4925 4927 4928 4933 4936

4937 4938 4939 4941 4942 4943 4946 4948 4952 4953 4955

4956 4958 4959 4962 4963 4964 4967 4969 4970 4972 4974

4978 4979 4980 4981 4983 4984 4985 4987 4988 4989 4991

4993 4999 5001 5003 5004 5005 5006 5007 5008 5009 5012

5013 5014 5015 5016 5017 5018 5019 5020 5022 5023 5026

5031 5032 5033 5034 5037 5038 5040 5044 5045 5046 5047

5048 5051 5052 5056 5057 5058 5059 5063 5064 5065 5066

5067 5069 5070 5071 5072 5079 5081 5082 5084 5085 5086

5088 5096 5097 5098 5100 5101 5102 5103 5104 5106 5107

5108 5109 5110 5111 5112 5113 5114 5115 5116 5117 5119

5122 5125 5126 5129 5130 5131 5133 5134 5136 5137 5138

5140 5143 5146 5147 5149 5150 5152 5153 5157 5162 5163

5165 5166 5167 5171 5172 5174 5175 5178 5179 5181 5184

5187 5189 5191 5193 5195 5200 5201 5203 5204 5206 5209

5213 5215 5216 5220 5221 5222 5223 5224 5226 5229 5232

5234 5236 5238 5239 5240 5243 5246 5249 5250 5252 5253

5256 5260 5263 5264 5266 5271 5272 5273 5276 5277 5278

5283 5284 5285 5289 5290 5293 5294 5295 5299 5304 5307

5310 5314 5315 5316 5318 5319 5320 5324 5325 5327 5328

5329 5330 5331 5333 5338 5339 5341 5342 5344 5347 5351

5353 5354 5356 5358 5359 5360 5364 5366 5369 5371 5372

5373 5377 5378 5379 5380 5381 5383 5384 5386 5393 5394

5396 5397 5398 5399 5400 5403 5405 5408 5412 5414 5415

5416 5419 5420 5421 5423 5424 5425 5428 5430 5431 5434

5435 5440 5441 5442 5443 5444 5445 5446 5447 5448 5451

5452 5453 5454 5455 5463 5464 5466 5468 5471 5474 5475

5477 5478 5483 5485 5486 5487 5491 5493 5494 5497 5498

5501 5502 5504 5505 5509 5511 5512 5513 5514 5515 5518

5521 5522 5525 5526 5527 5529 5533 5536 5538 5540 5541

5542 5544 5545 5547 5548 5549 5550 5551 5552 5554 5556

5557 5559 5560 5562 5563 5565 5567 5568 5570 5571 5572

5573 5574 5576 5578 5580 5581 5583 5585 5586 5587 5588

5589 5590 5591 5592 5593 5594 5597 5601 5603 5607 5610

5614 5616 5619 5621 5622 5625 5626 5627 5630 5632 5635

5638 5639 5640 5642 5643 5644 5648 5652 5653 5654 5656

5657 5658 5659 5661 5664 5665 5666 5668 5669 5673 5674

5675 5678 5679 5681 5684 5686 5687 5688 5690 5691 5692

5693 5694 5696 5698 5702 5703 5704 5706 5707 5710 5716

5718 5719 5720 5722 5724 5726 5729 5730 5731 5733 5735

5737 5739 5740 5741 5742 5743 5745 5746 5748 5749 5752

5753 5754 5755 5757 5759 5760 5761 5762 5764 5766 5768

5769 5771 5772 5773 5777 5778 5779 5781 5785 5786 5788

5789 5790 5792 5798 5799 5801 5802 5808 5809 5810 5811

5812 5815 5816 5818 5822 5824 5827 5830 5831 5833 5839

002

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REVISION No.: 01 - Apr 07/15 Page: 21

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SERVICE BULLETIN

MSN CONFIGURATION

5841 5842 5843 5844 5845 5846 5848 5849 5851 5855 5859

5862 5863 5866 5867 5869 5872 5873 5874 5876 5878 5879

5881 5883 5886 5887 5888 5889 5891 5897 5901 5902 5903

5905 5906 5907 5908 5911 5912 5913 5914 5917 5918 5919

5921 5925 5926 5927 5929 5931 5933 5934 5935 5943 5945

5950 5957 5959 5963 5965 5966 5967 5969 5970 5972 5973

5974 5976 5981 5982 5984 5989 5990 5995 5997 6000 6003

6004 6005 6006 6011 6012 6013 6015 6016 6017 6021 6022

6024 6025 6026 6033 6034 6038 6039 6040 6041 6042 6043

6044 6045 6047 6048 6050 6051 6053 6054 6055 6056 6057

6060 6061 6064 6065 6066 6067 6069 6071 6072 6073 6075

6079 6080 6081 6084 6085 6087 6088 6090 6092 6095 6096

6102 6103 6105 6107 6110 6111 6112 6114 6116 6117 6118

6119 6122 6124 6125 6127 6135 6139 6141 6144 6145 6149

6150 6151 6153 6154 6156 6157 6158 6160 6164 6166 6167

6168 6169 6170 6171 6172 6173 6174 6176 6177 6178 6179

6183 6184 6188 6192 6196 6202 6204 6206 6207 6209 6210

6213 6215 6216 6218 6220 6221 6224 6225 6231 6232 6234

6239 6240 6242 6243 6244 6246 6248 6250 6251 6257 6258

6259 6260 6262 6263 6265 6267 6268 6269 6270 6274 6276

6277 6280 6281 6282 6283 6285 6292 6293 6301 6307 6309

6310 6312 6314 6315 6317 6318 6319 6320 6322 6323 6325

6328 6329 6333 6335 6338 6339 6341 6342 6347 6348 6349

6350 6351 6353 6355 6356 6357 6358 6361 6364 6365 6367

6368 6369 6372 6373 6375 6376 6378 6379 6380 6384 6386

6389 6391 6392 6393 6397 6398 6403 6404 6405 6406 6408

6409 6410 6411 6412 6413 6414 6416 6418 6422 6423 6428

6429 6430 6432 6433 6434 6435 6437 6438 6441 6442 6444

6446 6447 6452 6453 6454 6456 6457 6458 6459 6465 6466

6467 6468 6469 6476 6477 6481 6484 6485 6488 6491 6492

6494 6496 6497 6498 6500 6501 6502 6503 6505 6509 6511

6514 6515 6516 6519 6521 6524 6525 6526 6528 6529 6536

6538 6540 6541 6542 6545 6546 6547 6548 6549 6550 6552

6553 6561 6562 6564 6565 6567 6568 6570 6572 6577 6579

6582 6584 6585 6587 6588 6590 6591 6592 6595 6596 6597

6598 6600 6603 6605 6606 6608 6615 6617 6619 6622 6626

6627 6628 6629 6632 6633 6634 6636 6637 6639 6640 6641

6644 6646 6648 6651 6653 6654 6658 6661 6664 6665 6666

6669 6670 6671 6674 6675 6676 6677 6678 6679 6680 6681

6685 6686 6689 6690 6692 6695 6696 6697 6698 6699 6701

6702 6704 6707 6708 6710 6712 6713 6714 6715 6716 6717

6718 6719 6721 6722 6724 6726 6727 6728 6729 6730 6732

6737 6738 6739 6741 6742 6743 6746 6747 6753 6754 6756

6759 6762 6764 6765 6767 6769 6773 6776 6777 6779 6780

6782 6784 6786 6787 6788 6789 6793 6797 6798 6800 6803

6805 6806 6807 6808 6811 6813 6814 6815 6817 6823 6824

6825 6826 6830 6831 6834 6835 6836 6837 6838 6843 6844

6845 6846 6847 6852 6855 6856 6858 6862 6870 6871 6872

6873 6874 6876 6877 6878 6879 6881 6884 6885 6889 6890

6891 6892 6893 6894 6895 6896 6899 6900 6902 6905 6911

6916 6918 6921 6922 6923 6924 6925 6926 6927 6929

002

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REVISION No.: 01 - Apr 07/15 Page: 22

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SERVICE BULLETIN

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft fitted with CFM56-5A engines.

**CONF 002

Config. 002 is valid for aircraft fitted with CFM56-5B engines.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Equipment BFEA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During scheduled inspections, some operators have reported damage on the Aft Engine

Mount Inner Retainer Brackets fitted on A320 Family Aircraft powered by CFM56-5A/-5B

engines.

The Inner Retainer Bracket provides a locking feature to the two nuts of the inner and

outer pins attaching the Aft Links to the Aft Mount Beam (also named Aft Engine Mount).

The same Retainer is used for the three Link Assemblies of the Aft Engine Mount. In

case of broken Inner Retainer Bracket, the locking feature is lost and knowing that these

Nuts are not self-locked, they could become loose. Subsequently, the Pins can also

loosen and the Aft Mount Link would be no longer secured to the Aft Engine Mount. In

this condition, the certification loads cannot be sustained anymore.

The outcome of investigations confirmed that the Retainer damage is due to the fatigue

cracking mechanism resulting from the dynamic effect of Engine vibrations.

On March 2013, the Alert Operators Transmission (AOT) A71N001-12 and UTAS

Service Bulletin No. RA32071-146, rendered mandatory by EASA Airworthiness Directive

(AD) No. 2013-0050, requested one time inspection for damaged Inner Retainer

Brackets and the replacement of nonconforming "Dull" surface finish Retainers by the

"Bright" surface finish Retainers. The nonconforming "Dull" surface finish was more

prone to pitting corrosion and which facilitated crack initiation.

However the main cause of crack initiation remains the vibration dynamic effect that

affects both Retainers with "Dull" and "Bright" surface finishes. The nonconforming "Dull"

surface’s pitting corrosion is an aggravating factor.

In addition the UTAS Service Bulletin No. RA32071-160 was published to advise

repetitive inspections of the affected Aft Engine Mount Retainer Brackets.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 23

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SERVICE BULLETIN

(2) Objective/Action

This Inspection Service Bulletin details a periodic inspection of the Aft Engine Mount

Retainers to be accomplished within the threshold and interval mentioned in the

PLANNING INFORMATION paragraph 1.E.

(3) Advantages

Accomplishment of this Inspection Service Bulletin will allow an early detection of

any potential damage on the Aft Mount Retainers and will avoid additional heavy

maintenance operation. This repetitive inspection is required up to the availability of the

final fix solution.

(4) Operational/Maintenance Consequences

The operational/maintenance consequences of this Service Bulletin are covered by

the update of the affected publications included in the PLANNING INFORMATION

paragraph 1.K.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 711060-832-801-001: Detailed Inspection of the Aft Engine Mount Inner Retainer

Brackets for Engine 1 and Engine 2

(1) Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets for Engine 1

(2) Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets for Engine 2

(3) If necessary, Remove the Center Aft Engine Mount Inner Retainer Bracket on Engine

1

(4) If necessary, Remove the Left Aft Engine Mount Inner Retainer Bracket on Engine 1

(5) If necessary, Remove the Right Aft Engine Mount Inner Retainer Bracket on Engine

1

(6) If necessary, Remove the Center Aft Engine Mount Inner Retainer Bracket on Engine

2

(7) If necessary, Remove the Left Aft Engine Mount Inner Retainer Bracket on Engine 2

(8) If necessary, Remove the Right Aft Engine Mount Inner Retainer Bracket on Engine

2

(9) If Removed, Install the Center Aft Engine Mount Inner Retainer Bracket on Engine 1

(10) If Removed, Install the Left Aft Engine Mount Inner Retainer Bracket on Engine 1

(11) If Removed, Install the Right Aft Engine Mount Inner Retainer Bracket on Engine 1

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 24

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(12) If Removed, Install the Center Aft Engine Mount Inner Retainer Bracket on Engine 2

(13) If Removed, Install the Left Aft Engine Mount Inner Retainer Bracket on Engine 2

(14) If Removed, Install the Right Aft Engine Mount Inner Retainer Bracket on Engine 2

(15) Torque check

**CONF 002

Task 711060-832-801-001: Detailed Inspection of the Aft Engine Mount Inner Retainer

Brackets for Engine 1 and Engine 2

(1) Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets for Engine 1

(2) Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets for Engine 2

(3) If necessary, Remove the Center Aft Engine Mount Inner Retainer Bracket on Engine

1

(4) If necessary, Remove the Left Aft Engine Mount Inner Retainer Bracket on Engine 1

(5) If necessary, Remove the Right Aft Engine Mount Inner Retainer Bracket on Engine

1

(6) If necessary, Remove the Center Aft Engine Mount Inner Retainer Bracket on Engine

2

(7) If necessary, Remove the Left Aft Engine Mount Inner Retainer Bracket on Engine 2

(8) If necessary, Remove the Right Aft Engine Mount Inner Retainer Bracket on Engine

2

(9) If Removed, Install the Center Aft Engine Mount Inner Retainer Bracket on Engine 1

(10) If Removed, Install the Left Aft Engine Mount Inner Retainer Bracket on Engine 1

(11) If Removed, Install the Right Aft Engine Mount Inner Retainer Bracket on Engine 1

(12) If Removed, Install the Center Aft Engine Mount Inner Retainer Bracket on Engine 2

(13) If Removed, Install the Left Aft Engine Mount Inner Retainer Bracket on Engine 2

(14) If Removed, Install the Right Aft Engine Mount Inner Retainer Bracket on Engine 2

(15) Torque check

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 25

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(2) Accomplishment Timescale

**CONF 001

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

Table 1, Config. 001 - Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets for Engine

1 and Engine 2

Compliance time

(whichever occurs

later)

Condition Action

Threshold (whichever

occurs later)

Repetitive interval

(whichever occurs

first)

All aircraft Do a detailed inspection of the

aft engine mount inner retainer

brackets for engine 1 and

engine 2, in accordance with

TASK 711060-832-801-001

12 months since the

aircraft first flight or

new Retainer Bracket

installation or SB initial

issue date

None

Replace the affected dull

retainer bracket(s) on engine 1

and/or engine 2, in accordance

with SUBTASK

711060-000-001-001 thru

SUBTASK 71160-000-006-001

for the removal and SUBTASK

711060-400-001-001 thru

SUBTASK 711060-400-006-001

for the installation

AND

All aircraft with AOT

A71N001-12 not

performed and dull aft

engine mount inner

retainer brackets not

replaced

Do a detailed inspection of the

aft engine mount inner retainer

bracket for engine 1 and engine

2, in accordance with TASK

711060-832-801-001

Before next flight None

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 26

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Table 1, Config. 001 - Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets for Engine

1 and Engine 2

Compliance time

(whichever occurs

later)

Condition Action

Threshold (whichever

occurs later)

Repetitive interval

(whichever occurs

first)

Replace the affected retainer

bracket, in accordance with

SUBTASK 711060-000-001-001

thru SUBTASK

71160-000-006-001 for the

removal and SUBTASK

711060-400-001-001 thru

SUBTASK 711060-400-006-001

for the installation

AND

Contact AIRBUS

AND

Any retainer bracket Before next flight None

found missing,

damaged, cracked or

broken

Repeat the detailed inspection

of the aft engine mount inner

retainer brackets for engine 1

and engine 2, in accordance

with TASK 711060-832-801-001

None 12 months

No retainer bracket

found missing,

damaged, cracked or

broken

Repeat the detailed inspection

of the aft engine mount inner

retainer brackets for engine 1

and engine 2, in accordance

with TASK 711060-832-801-001

None 12 months

**CONF 002

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

Table 1, Config. 002 - Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets for Engine

1 and Engine 2

Compliance time

(whichever occurs

later)

Condition Action

Threshold (whichever

occurs later)

Repetitive interval

(whichever occurs

first)

All aircraft Do a detailed inspection of the

aft engine mount inner retainer

brackets for engine 1 and

engine 2, in accordance with

TASK 711060-832-801-001

12 months since the

aircraft first flight or

new Retainer Bracket

installation or SB

initial issue date

None

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 27

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Table 1, Config. 002 - Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets for Engine

1 and Engine 2

Compliance time

(whichever occurs

later)

Condition Action

Threshold (whichever

occurs later)

Repetitive interval

(whichever occurs

first)

Replace the affected dull

retainer bracket(s) on engine 1

and/or engine 2, in accordance

with SUBTASK

711060-000-001-002 thru

SUBTASK 71160-000-006-002

for the removal and SUBTASK

711060-400-001-002 thru

SUBTASK 711060-400-006-002

for the installation

AND

All aircraft with AOT

A71N001-12 not

performed and dull aft

engine mount inner

retainer brackets not

replaced

Do a detailed inspection of the

aft engine mount inner retainer

bracket for engine 1 and engine

2, in accordance with TASK

711060-832-801-001

Before next flight None

Replace the affected retainer

bracket, in accordance with

SUBTASK 711060-000-001-002

thru SUBTASK

71160-000-006-002 for the

removal and SUBTASK

711060-400-001-002 thru

SUBTASK 711060-400-006-002

for the installation

AND

Contact AIRBUS

AND

Any retainer bracket Before next flight None

found missing,

damaged, cracked or

broken

Repeat the detailed inspection

of the aft engine mount inner

retainer brackets for engine 1

and engine 2, in accordance

with TASK 711060-832-801-001

None 12 months

No retainer bracket

found missing,

damaged, cracked or

broken

Repeat the detailed inspection

of the aft engine mount inner

retainer brackets for engine 1

and engine 2, in accordance

with TASK 711060-832-801-001

None 12 months

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 28

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**CONF ALL

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organization Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

**CONF 001

Task 711060-832-801-001: Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets

for Engine 1 and Engine 2

Get Access 1.00

On Aircraft

Detailed Inspection of the Aft Engine Mount Inner

Retainer Brackets for Engine 1

0.50

Detailed Inspection of the Aft Engine Mount Inner

Retainer Brackets for Engine 2

0.50

If necessary, Remove the Center Aft Engine Mount

Inner Retainer Bracket on Engine 1

0.50

If necessary, Remove the Left Aft Engine Mount Inner

Retainer Bracket on Engine 1

0.50

If necessary, Remove the Right Aft Engine Mount Inner

Retainer Bracket on Engine 1

0.50

If necessary, Remove the Center Aft Engine Mount

Inner Retainer Bracket on Engine 2

0.50

If necessary, Remove the Left Aft Engine Mount Inner

Retainer Bracket on Engine 2

0.50

If necessary, Remove the Right Aft Engine Mount Inner

Retainer Bracket on Engine 2

0.50

If Removed, Install the Center Aft Engine Mount Inner

Retainer Bracket on Engine 1

0.50

If Removed, Install the Left Aft Engine Mount Inner

Retainer Bracket on Engine 1

0.50

If Removed, Install the Right Aft Engine Mount Inner

Retainer Bracket on Engine 1

0.50

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 29

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Task 711060-832-801-001: Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets

for Engine 1 and Engine 2

If Removed, Install the Center Aft Engine Mount Inner

Retainer Bracket on Engine 2

0.50

If Removed, Install the Left Aft Engine Mount Inner

Retainer Bracket on Engine 2

0.50

If Removed, Install the Right Aft Engine Mount Inner

Retainer Bracket on Engine 2

0.50

Torque check 0.50

Close-Up 1.00

TOTAL MANHOURS 9.50

ELAPSED TIME (HOURS) 1.50

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt

Chart, Fig. A-FAAAA given in Appendix 01 - Elapsed Time Assumption .

**CONF 002

Task 711060-832-801-001: Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets

for Engine 1 and Engine 2

Get Access 1.00

On Aircraft

Detailed Inspection of the Aft Engine Mount Inner

Retainer Brackets for Engine 1

0.50

Detailed Inspection of the Aft Engine Mount Inner

Retainer Brackets for Engine 2

0.50

If necessary, Remove the Center Aft Engine Mount

Inner Retainer Bracket on Engine 1

0.50

If necessary, Remove the Left Aft Engine Mount Inner

Retainer Bracket on Engine 1

0.50

If necessary, Remove the Right Aft Engine Mount Inner

Retainer Bracket on Engine 1

0.50

If necessary, Remove the Center Aft Engine Mount

Inner Retainer Bracket on Engine 2

0.50

If necessary, Remove the Left Aft Engine Mount Inner

Retainer Bracket on Engine 2

0.50

If necessary, Remove the Right Aft Engine Mount Inner

Retainer Bracket on Engine 2

0.50

If Removed, Install the Center Aft Engine Mount Inner

Retainer Bracket on Engine 1

0.50

If Removed, Install the Left Aft Engine Mount Inner

Retainer Bracket on Engine 1

0.50

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 30

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Task 711060-832-801-001: Detailed Inspection of the Aft Engine Mount Inner Retainer Brackets

for Engine 1 and Engine 2

If Removed, Install the Right Aft Engine Mount Inner

Retainer Bracket on Engine 1

0.50

If Removed, Install the Center Aft Engine Mount Inner

Retainer Bracket on Engine 2

0.50

If Removed, Install the Left Aft Engine Mount Inner

Retainer Bracket on Engine 2

0.50

If Removed, Install the Right Aft Engine Mount Inner

Retainer Bracket on Engine 2

0.50

Torque check 0.50

Close-Up 1.00

TOTAL MANHOURS 9.50

ELAPSED TIME (HOURS) 1.50

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt

Chart, Fig. A-FAAAA given in Appendix 01 - Elapsed Time Assumption .

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Airworthiness Directive (AD) 2013-0050

Aircraft Maintenance Manual (AMM) 06-20-00 12-34-24 20-21-11

27-50-00 71-13-00 71-22-11

78-36-00

Elec. Std. Practices Manual (ESPM) 20-55-00

**CONF 002

Airworthiness Directive (AD) 2013-0050

Aircraft Maintenance Manual (AMM) 06-20-00 12-34-24 20-21-11

27-50-00 71-13-00 71-22-11

78-36-00

Elec. Std. Practices Manual (ESPM) 20-55-00

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 31

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**CONF ALL

K. PUBLICATION AFFECTED

Impact on scheduled maintenance: Refer to MPD

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

Inner Retainer Bracket 238-0252-505

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 32

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Vendor parts are to be procured from:

Equipment BFEA01 UTAS Aerostructures

850 Lagoon Drive

Chula Vista

CA 91910-2098

USA

Phone: +1-860-654-2500

Fax: +1-860-660-0372

E-Mail: CRC@utas.utc.com

internet: www.utascrc.com

(2) Price and Availability

Equipment BFEA01

No AIRBUS kit will be provided.

Procurement terms for the equipment must be negotiated with the equipment supplier.

B. INDUSTRY SUPPORT INFORMATION

Industry support terms for the equipment must be negotiated with the equipment supplier.

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

None

(2) Components

None

(3) Equipment

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

8 238-0252-505 6 RETAINER (1)

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 33

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NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

NOTE: To accomplish this Service Bulletin it is necessary to use the tools listed

in the subsequent referenced AMM tasks:

- AMM Task 78-36-00-010-040

- AMM Task 78-36-00-410-040

- AMM Task 71-22-11-400-042 for aircraft fitted with CFM56-5A

engine

- AMM Task 71-22-11-400-043 for aircraft fitted with CFM56-5B

engine

- AMM Task 71-22-11-000-042 for aircraft fitted with CFM56-5A

engine

- AMM Task 71-22-11-000-043 for aircraft fitted with CFM56-5B

engine

(3) Special Tools

None

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 34

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 711060-832-801-001 - Detailed Inspection of the Aft Engine Mount Inner Retainer

Brackets for Engine 1 and Engine 2

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin include procedures given

in other documents or in other sections of the Service Bulletin. When the words

"refer to" are used and the operator has a procedure accepted by the local

authority he belongs to, the accepted alternative procedure can be used. When the

words "in accordance with" are used then the given procedure must be followed.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: The purpose of flow charts is to supplement the information given in the Procedure

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 35

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NOTE: Discarded parts must be managed at the operator’s discretion.

Task Associated Data

**CONF 001

Zone

450 460

Access

Door 437AL 438AR 447AL 448AR 451AL 452AR 461AL 462AR

Manpower

TOTAL MANHOURS 9.50

ELAPSED TIME (HOURS) 1.50

**CONF 002

Zone

450 460

Access

Door 437AL 438AR 447AL 448AR 451AL 452AR 461AL 462AR

Manpower

TOTAL MANHOURS 9.50

ELAPSED TIME (HOURS) 1.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 711060-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

Task 20-21-11-911-001

(a) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(b) Tag all the parts you must remove and retain to make the subsequent installation

easier.

(c) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(d) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-001.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 36

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(2) Subtask 711060-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 002

(1) Subtask 711060-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

Task 20-21-11-911-001

(a) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(b) Tag all the parts you must remove and retain to make the subsequent installation

easier.

(c) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(d) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-001.

(2) Subtask 711060-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 711060-941-001-001 - Get access for Engine 1

Work Zones and Access Panels

Zone Access/Work location

450

Manpower Resources

Skills ENGINE

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 37

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References

Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 27-50-00-866-009

Task 71-13-00-010-040

Task 78-36-00-010-040

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-869-002.

(b) Put an access platform in position.

(c) Make sure that the retract the flaps and the slats on the ground, refer to AMM Task

27-50-00-866-009.

(d) Open the Fan Cowl Doors, refer to AMM Task 71-13-00-010-040.

(e) Open the Thrust Reverser Doors to the 45 degree position, refer to AMM Task

78-36-00-010-040.

(2) Subtask 711060-941-002-001 - Get access for Engine 2

Work Zones and Access Panels

Zone Access/Work location

460

Manpower Resources

Skills ENGINE

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 38

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References

Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 27-50-00-866-009

Task 71-13-00-010-040

Task 78-36-00-010-040

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-869-002.

(b) Put an access platform in position.

(c) Make sure that the retract the flaps and the slats on the ground, refer to AMM Task

27-50-00-866-009.

(d) Open the Fan Cowl Doors, refer to AMM Task 71-13-00-010-040.

(e) Open the Thrust Reverser Doors to the 45 degree position, refer to AMM Task

78-36-00-010-040.

**CONF 002

(1) Subtask 711060-941-001-001 - Get access for Engine 1

Work Zones and Access Panels

Zone Access/Work location

450

Manpower Resources

Skills ENGINE

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 39

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References

Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 27-50-00-866-009

Task 71-13-00-010-040

Task 78-36-00-010-040

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-869-002.

(b) Put an access platform in position.

(c) Make sure that the retract the flaps and the slats on the ground, refer to AMM Task

27-50-00-866-009.

(d) Open the Fan Cowl Doors, refer to AMM Task 71-13-00-010-040.

(e) Open the Thrust Reverser Doors to the 45 degree position, refer to AMM Task

78-36-00-010-040.

(2) Subtask 711060-941-002-001 - Get access for Engine 2

Work Zones and Access Panels

Zone Access/Work location

460

Manpower Resources

Skills ENGINE

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 40

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 27-50-00-866-009

Task 71-13-00-010-040

Task 78-36-00-010-040

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-869-002.

(b) Put an access platform in position.

(c) Make sure that the retract the flaps and the slats on the ground, refer to AMM Task

27-50-00-866-009.

(d) Open the Fan Cowl Doors, refer to AMM Task 71-13-00-010-040.

(e) Open the Thrust Reverser Doors to the 45 degree position, refer to AMM Task

78-36-00-010-040.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 41

5

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**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 711060-832-001-001 - Detailed Inspection of the Aft Engine Mount Inner

Retainer Brackets for Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Fig. A-FFAAA

Flow Chart

Sheet 01

Fig. A-FBAAA

Inspection of the three Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

(a) At the threshold given in PLANNING INFORMATION paragraph E.(2):

Do a detailed inspection of the left, center and right Aft Engine Mount Inner

Retainer Brackets for the Engine 1.

Refer to Fig. A-FFAAA

NOTE: Identify the most visible surfaces of each Aft Engine Mount Inner

Retainer Brackets (3 locations) and clean these areas before

performing the detailed inspection.

NOTE: Use 10x magnifier, mirror and light to inspect the left, center and

right Aft Engine Mount Inner Retainer Brackets.

NOTE: The center Aft Engine Mount Inner Retainer Bracket may be difficult

to inspect visually, then an articulated fiberscope can be used as a

help. In case of doubt, remove the center Aft Engine Mount Inner

Retainer Bracket for inspection.

Refer to SUBTASK 711060-000-001 001 If necessary, Remove the

Center Aft Engine Mount Inner Retainer Bracket on Engine 1 .

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 42

5

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SERVICE BULLETIN

1 If AOT A71N001-12 is performed and dull Aft Engine Mount Inner Retainer

Brackets are replaced:

a Do a detailed inspection of the left, center and right Aft Engine Mount

Inner Retainer Brackets for the Engine 1.

Refer to Fig. A-FBAAA

<1> If any Inner Retainer Bracket is found damaged, cracked, broken or

missing:

<a> Before next flight, replace as required the affected

Inner Retainer Brackets, in accordance with SUBTASK

711060-000-001 001 If necessary, Remove the Center Aft

Engine Mount Inner Retainer Bracket on Engine 1 thru

SUBTASK 711060-000-004 001 If necessary, Remove the

Right Aft Engine Mount Inner Retainer Bracket on Engine 1 for

the removal and SUBTASK 711060-400-001 001 If Removed,

Install the Center Aft Engine Mount Inner Retainer Bracket on

Engine 1 thru SUBTASK 711060-400-004 001 If Removed,

Install the Right Aft Engine Mount Inner Retainer Bracket on

Engine 1 for the installation.

<b> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 1 at the

interval given in PLANNING INFORMATION paragraph E.(2).

<2> If Inner Retainer Brackets are not found damaged, cracked, broken

or missing:

<a> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 1 at the

interval given in PLANNING INFORMATION paragraph E.(2).

b Send the Inspection Report to AIRBUS, refer to Fig. A-FRAAA.

2 If AOT A71N001-12 is not performed and dull Aft Engine Mount Inner Retainer

Brackets are not replaced:

a Before next flight, replace as required the affected dull Inner

Retainer Brackets, in accordance with SUBTASK 711060-000-001 001

If necessary, Remove the Center Aft Engine Mount Inner Retainer

Bracket on Engine 1 thru SUBTASK 711060-000-004 001 If necessary,

Remove the Right Aft Engine Mount Inner Retainer Bracket on Engine 1

for the removal and SUBTASK 711060-400-001 001 If Removed, Install

the Center Aft Engine Mount Inner Retainer Bracket on Engine 1 thru

SUBTASK 711060-400-004 001 If Removed, Install the Right Aft Engine

Mount Inner Retainer Bracket on Engine 1 for the installation.

and

Do a detailed inspection of the left, center and right Aft Engine Mount

Inner Retainer Brackets for the Engine 1.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 43

5

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Refer to Fig. A-FBAAA

<1> If any Inner Retainer Bracket is found damaged, cracked, broken or

missing:

<a> Before next flight, replace as required the affected

Inner Retainer Brackets, in accordance with SUBTASK

711060-000-001 001 If necessary, Remove the Center Aft

Engine Mount Inner Retainer Bracket on Engine 1 thru

SUBTASK 711060-000-004 001 If necessary, Remove the

Right Aft Engine Mount Inner Retainer Bracket on Engine 1 for

the removal and SUBTASK 711060-400-001 001 If Removed,

Install the Center Aft Engine Mount Inner Retainer Bracket on

Engine 1 thru SUBTASK 711060-400-004 001 If Removed,

Install the Right Aft Engine Mount Inner Retainer Bracket on

Engine 1 for the installation.

<b> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 1 at the

interval given in PLANNING INFORMATION paragraph E.(2).

<2> If Inner Retainer Brackets are not found damaged, cracked, broken

or missing:

<a> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 1 at the

interval given in PLANNING INFORMATION paragraph E.(2).

b Send the Inspection Report to AIRBUS, refer to Fig. A-FRAAA.

NOTE: If removed, install the center Aft Engine Mount Inner Retainer Bracket.

Refer to SUBTASK 711060-400-001 001 If Removed, Install the Center

Aft Engine Mount Inner Retainer Bracket on Engine 1 .

(2) Subtask 711060-832-002-001 - Detailed Inspection of the Aft Engine Mount Inner

Retainer Brackets for Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Fig. A-FFAAA

Flow Chart

Sheet 01

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 44

5

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SERVICE BULLETIN

References

Fig. A-FBAAA

Inspection of the three Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

(a) At the threshold given in PLANNING INFORMATION paragraph E.(2):

Do a detailed inspection of the left, center and right Aft Engine Mount Inner

Retainer Brackets for the Engine 2.

Refer to Fig. A-FFAAA

NOTE: Identify the most visible surfaces of each Aft Engine Mount Inner

Retainer Brackets and clean these areas before performing the

detailed inspection.

NOTE: Use 10x magnifier, mirror and light to inspect the left, center and

right Aft Engine Mount Inner Retainer Brackets.

NOTE: The center Aft Engine Mount Inner Retainer Bracket may be difficult

to inspect visually, then an articulated fiberscope can be used as a

help. In case of doubt, remove the center Aft Engine Mount Inner

Retainer Bracket for inspection.

Refer to SUBTASK 711060-000-001 001 If necessary, Remove the

Center Aft Engine Mount Inner Retainer Bracket on Engine 1 .

1 If AOT A71N001-12 is performed and dull Aft Engine Mount Inner Retainer

Brackets are replaced:

a Do a detailed inspection of the left, center and right Aft Engine Mount

Inner Retainer Brackets for the Engine 2.

Refer to Fig. A-FBAAA

<1> If any Inner Retainer Bracket is found damaged, cracked, broken or

missing:

<a> Before next flight, replace as required the affected

Inner Retainer Bracket, in accordance with SUBTASK

711060-000-002 001 If necessary, Remove the Center Aft

Engine Mount Inner Retainer Bracket on Engine 2 thru

SUBTASK 711060-000-006 001 If necessary, Remove the

Right Aft Engine Mount Inner Retainer Bracket on Engine 2 for

the removal and SUBTASK 711060-400-002 001 If Removed,

Install the Center Aft Engine Mount Inner Retainer Bracket on

Engine 2 thru SUBTASK 711060-400-006 001 If Removed,

Install the Right Aft Engine Mount Inner Retainer Bracket on

Engine 2 for the installation.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 45

5

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<b> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 2 at the

interval given in PLANNING INFORMATION paragraph E.(2).

<2> If Inner Retainer Brackets are not found damaged, cracked, broken

or missing:

<a> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 2 at the

interval given in PLANNING INFORMATION paragraph E.(2).

b Send the Inspection Report to AIRBUS, refer to Fig. A-FRAAA.

2 If AOT A71N001-12 is not performed and dull Aft Engine Mount Inner Retainer

Brackets are not replaced:

a Before next flight, replace as required the affected dull Inner

Retainer Brackets, in accordance with SUBTASK 711060-000-002 001

If necessary, Remove the Center Aft Engine Mount Inner Retainer

Bracket on Engine 2 thru SUBTASK 711060-000-006 001 If necessary,

Remove the Right Aft Engine Mount Inner Retainer Bracket on Engine 2

for the removal and SUBTASK 711060-400-002 001 If Removed, Install

the Center Aft Engine Mount Inner Retainer Bracket on Engine 2 thru

SUBTASK 711060-400-006 001 If Removed, Install the Right Aft Engine

Mount Inner Retainer Bracket on Engine 2 for the installation.

and

Do a detailed inspection of the left, center and right Aft Engine Mount

Inner Retainer Brackets for the Engine 2.

Refer to Fig. A-FBAAA

<1> If any Inner Retainer Bracket is found damaged, cracked, broken or

missing:

<a> Before next flight, replace as required the affected

Inner Retainer Bracket, in accordance with SUBTASK

711060-000-002 001 If necessary, Remove the Center Aft

Engine Mount Inner Retainer Bracket on Engine 2 thru

SUBTASK 711060-000-006 001 If necessary, Remove the

Right Aft Engine Mount Inner Retainer Bracket on Engine 2 for

the removal and SUBTASK 711060-400-002 001 If Removed,

Install the Center Aft Engine Mount Inner Retainer Bracket on

Engine 2 thru SUBTASK 711060-400-006 001 If Removed,

Install the Right Aft Engine Mount Inner Retainer Bracket on

Engine 2 for the installation.

<b> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 2 at the

interval given in PLANNING INFORMATION paragraph E.(2).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 46

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<2> If Inner Retainer Brackets are not found damaged, cracked, broken

or missing:

<a> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 2 at the

interval given in PLANNING INFORMATION paragraph E.(2).

b Send the Inspection Report to AIRBUS, refer to Fig. A-FRAAA.

NOTE: If removed, install the center Aft Engine Mount Inner Retainer Bracket.

Refer to SUBTASK 711060-400-002 001 If Removed, Install the Center

Aft Engine Mount Inner Retainer Bracket on Engine 2 .

(3) Subtask 711060-000-001-001 - If necessary, Remove the Center Aft Engine Mount

Inner Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-042

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Without using the engine bootstrap system, remove the Center Aft Engine Mount

Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 47

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2 Bolt Item (6) Retain

2 Washer Item (7) Retain

2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

2 Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system

to support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

- Do the Job Set-up procedure paragraph 3.E Installation of

the Bootstrap System as specified in the Removal of the Aft

Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-000-042 and continue to the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

3 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

NOTE: Do not remove the pins Item (1) and (2) and the anti-rotation

bracket Item (3) from the link assembly Item (5) when you

remove the nuts Item (10) and (11).

(4) Subtask 711060-000-003-001 - If necessary, Remove the Left Aft Engine Mount

Inner Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 48

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Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-042

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Without using the engine bootstrap system, remove the Left Aft Engine Mount Inner

Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

2 Bolt Item (6) Retain

2 Washer Item (7) Retain

2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system to

support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 49

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- Do the Job Set-up procedure paragraph 3.E Installation of the Bootstrap

System as specified in the Removal of the Aft Engine Mount Without

Engine Removal, refer to AMM Task 71-22-11-000-042 and continue to

the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

2 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

NOTE: Do not remove the pins Item (1) and (2) and the anti-rotation

bracket Item (3) from the link assembly Item (5) when you

remove the nuts Item (10) and (11).

(5) Subtask 711060-000-004-001 - If necessary, Remove the Right Aft Engine Mount

Inner Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-042

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Without using the engine bootstrap system, remove the Right Aft Engine Mount

Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 50

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1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

2 Bolt Item (6) Retain

2 Washer Item (7) Retain

2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system to

support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

- Do the Job Set-up procedure paragraph 3.E Installation of the Bootstrap

System as specified in the Removal of the Aft Engine Mount Without

Engine Removal, refer to AMM Task 71-22-11-000-042 and continue to

the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

2 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

NOTE: Do not remove the pins Item (1) and (2) and the anti-rotation

bracket Item (3) from the link assembly Item (5) when you

remove the nuts Item (10) and (11).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 51

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(6) Subtask 711060-000-002-001 - If necessary, Remove the Center Aft Engine Mount

Inner Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-042

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Without using the engine bootstrap system, remove the Center Aft Engine Mount

Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

2 Bolt Item (6) Retain

2 Washer Item (7) Retain

2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 52

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2 Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system

to support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

- Do the Job Set-up procedure paragraph (3.E Installation of

the Bootstrap System) as specified in the Removal of the Aft

Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-000-042 and continue to the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

3 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

NOTE: Do not remove the pins Item (1) and (2) and the anti-rotation

bracket Item (3) from the link assembly Item (5) when you

remove the nuts Item (10) and (11).

(7) Subtask 711060-000-005-001 - If necessary, Remove the Left Aft Engine Mount

Inner Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-042

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 53

5

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(a) Without using the engine bootstrap system, remove the Left Aft Engine Mount Inner

Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

2 Bolt Item (6) Retain

2 Washer Item (7) Retain

2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

2 Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system

to support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

- Do the Job Set-up procedure paragraph 3.E Installation of

the Bootstrap System as specified in the Removal of the Aft

Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-000-042 and continue to the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

3 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 54

5

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NOTE: Do not remove the pins Item (1) and (2) and the anti-rotation

bracket Item (3) from the link assembly Item (5) when you

remove the nuts Item (10) and (11).

(8) Subtask 711060-000-006-001 - If necessary, Remove the Right Aft Engine Mount

Inner Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-042

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Without using the engine bootstrap system, remove the Right Aft Engine Mount

Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

2 Bolt Item (6) Retain

2 Washer Item (7) Retain

2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 55

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SERVICE BULLETIN

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system to

support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

- Do the Job Set-up procedure paragraph 3.E Installation of the Bootstrap

System as specified in the Removal of the Aft Engine Mount Without

Engine Removal, refer to AMM Task 71-22-11-000-042 and continue to

the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

2 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

NOTE: Do not remove the pins Item (1) and (2) item and the antirotation bracket Item (3) from the link assembly Item (5) when

you remove the nuts Item (10) and (11).

(9) Subtask 711060-400-001-001 - If Removed, Install the Center Aft Engine Mount

Inner Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 56

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-042

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Center Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum torque

value of 12.88 m.daN (95.00 lbf.ft).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 57

5

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SERVICE BULLETIN

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

NOTE: Do not torque the nut Item 11 more than the maximum torque

value of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-042.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 58

5

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@A318/A319/A320/A321

SERVICE BULLETIN

(10) Subtask 711060-400-003-001 - If Removed, Install the Left Aft Engine Mount Inner

Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-042

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Left Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 59

5

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SERVICE BULLETIN

- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum value

of 12.88 m.daN (95.00 lbf.ft).

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

NOTE: Do not torque the nut Item 10 more than the maximum value

of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 60

5

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@A318/A319/A320/A321

SERVICE BULLETIN

2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-042.

(11) Subtask 711060-400-004-001 - If Removed, Install the Right Aft Engine Mount Inner

Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-042

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 61

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

References

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Right Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum value

of 12.88 m.daN (95.00 lbf.ft).

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 62

5

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@A318/A319/A320/A321

SERVICE BULLETIN

NOTE: Do not torque the nut Item 11 more than the maximum value

of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-042.

(12) Subtask 711060-400-002-001 - If Removed, Install the Center Aft Engine Mount

Inner Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 63

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-042

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Center Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum value

of 12.88 m.daN (95.00 lbf.ft).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 64

5

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SERVICE BULLETIN

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

NOTE: Do not torque the nut Item 11 more than the maximum value

of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-042.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 65

5

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@A318/A319/A320/A321

SERVICE BULLETIN

(13) Subtask 711060-400-005-001 - If Removed, Install the Left Aft Engine Mount Inner

Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-042

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Left Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 66

5

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- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum value

of 12.88 m.daN (95.00 lbf.ft).

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

NOTE: Do not torque the nut Item 11 more than the maximum value

of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 67

5

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@A318/A319/A320/A321

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2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-042.

(14) Subtask 711060-400-006-001 - If Removed, Install the Right Aft Engine Mount Inner

Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-042

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 68

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

References

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Right Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum value

of 12.88 m.daN (95.00 lbf.ft).

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 69

5

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@A318/A319/A320/A321

SERVICE BULLETIN

NOTE: Do not torque the nut Item 11 more than the maximum value

of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-042.

(15) Subtask 711060-831-001-001 - Torque check

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

NOTE: Before starting the torque check, apply two lines of ink across nuts Item

(10) and (11) to bolts Item (1) and (2).

(a) Check the existing torque by turning the nuts counter-clockwise slowly in the

removal direction until the point of torque release.

NOTE: Check the torque of the nuts Item (10) and (11), by using a torque

wrench with an open-end type adapter or a torque wrench with a

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 70

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SERVICE BULLETIN

socket. The socket can be no longer than 51.51 mm (2.04 in.).

(b) Re-torque the nut Item (10) to match the ink lines and read the torque. The torque

value must be between 10.85 m.daN (80.00 lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

NOTE: Make sure the pin head is aligned with the slot in the retainer prior

to re-torque.

(c) Re-torque the nut Item (11) to match the ink lines and read the torque. The torque

value must be between 4.75 m.daN (35.00 lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

NOTE: Make sure the pin head is aligned with the slot in the retainer prior

to re-torque.

(d) If the nut torque is incorrect contact AIRBUS for reporting purpose.

**CONF 002

(1) Subtask 711060-832-001-002 - Detailed Inspection of the Aft Engine Mount Inner

Retainer Brackets for Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Fig. A-FFAAB

Flow Chart

Sheet 01

Fig. A-FBAAA

Inspection of the three Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

(a) At the threshold given in PLANNING INFORMATION paragraph E.(2):

Do a detailed inspection of the left, center and right Aft Engine Mount Inner

Retainer Brackets for the Engine 1.

Refer to Fig. A-FFAAB

NOTE: Identify the most visible surfaces of each Aft Engine Mount Inner

Retainer Brackets and clean these areas before performing the

detailed inspection.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 71

5

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SERVICE BULLETIN

NOTE: Use 10x magnifier, mirror and light to inspect the left, center and

right Aft Engine Mount Inner Retainer Brackets.

NOTE: The center Aft Engine Mount Inner Retainer Bracket may be difficult

to inspect visually, then an articulated fiberscope can be used as a

help. In case of doubt, remove the center Aft Engine Mount Inner

Retainer Bracket for inspection.

Refer to SUBTASK 711060-000-001 002 If necessary, Remove the

Center Aft Engine Mount Inner Retainer Bracket on Engine 1 .

1 If AOT A71N001-12 is performed and dull Aft Engine Mount Inner Retainer

Brackets are replaced:

a Do a detailed inspection of the left, center and right Aft Engine Mount

Inner Retainer Brackets for the Engine 1.

Refer to Fig. A-FBAAA

<1> If any Inner Retainer Bracket is found damaged, cracked, broken or

missing:

<a> Before next flight, replace as required the affected

Inner Retainer Bracket, in accordance with SUBTASK

711060-000-001 002 If necessary, Remove the Center Aft

Engine Mount Inner Retainer Bracket on Engine 1 thru

SUBTASK 711060-000-004 002 If necessary, Remove the

Right Aft Engine Mount Inner Retainer Bracket on Engine 1 for

the removal and SUBTASK 711060-400-001 002 If Removed,

Install the Center Aft Engine Mount Inner Retainer Bracket on

Engine 1 thru SUBTASK 711060-400-004 002 If Removed,

Install the Right Aft Engine Mount Inner Retainer Bracket on

Engine 1 for the installation.

<b> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 1 at the

interval given in PLANNING INFORMATION paragraph E.(2).

<2> If Inner Retainer Brackets are not found damaged, cracked, broken

or missing:

<a> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 1 at the

interval given in PLANNING INFORMATION paragraph E.(2).

b Send the Inspection Report to AIRBUS, refer to Fig. A-FRAAA.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 72

5

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2 If AOT A71N001-12 is not performed and dull Aft Engine Mount Inner Retainer

Brackets are not replaced:

a Before next flight, replace as required the affected dull Inner Retainer

Bracket, in accordance with SUBTASK 711060-000-001 002 If necessary,

Remove the Center Aft Engine Mount Inner Retainer Bracket on Engine 1

thru SUBTASK 711060-000-004 002 If necessary, Remove the Right

Aft Engine Mount Inner Retainer Bracket on Engine 1 for the removal

and SUBTASK 711060-400-001 002 If Removed, Install the Center Aft

Engine Mount Inner Retainer Bracket on Engine 1 thru SUBTASK

711060-400-004 002 If Removed, Install the Right Aft Engine Mount

Inner Retainer Bracket on Engine 1 for the installation.

and

Do a detailed inspection of the left, center and right Aft Engine Mount

Inner Retainer Brackets for the Engine 1.

Refer to Fig. A-FBAAA

<1> If any Inner Retainer Bracket is found damaged, cracked, broken or

missing:

<a> Before next flight, replace as required the affected

Inner Retainer Bracket, in accordance with SUBTASK

711060-000-001 002 If necessary, Remove the Center Aft

Engine Mount Inner Retainer Bracket on Engine 1 thru

SUBTASK 711060-000-006 002 If necessary, Remove the

Right Aft Engine Mount Inner Retainer Bracket on Engine 2 for

the removal and SUBTASK 711060-400-001 002 If Removed,

Install the Center Aft Engine Mount Inner Retainer Bracket on

Engine 1 thru SUBTASK 711060-400-006 002 If Removed,

Install the Right Aft Engine Mount Inner Retainer Bracket on

Engine 2 for the installation.

<b> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 1 at the

interval given in PLANNING INFORMATION paragraph E.(2).

<2> If Inner Retainer Brackets are not found damaged, cracked, broken

or missing:

<a> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 1 at the

interval given in PLANNING INFORMATION paragraph E.(2).

b Send the Inspection Report to AIRBUS, refer to Fig. A-FRAAA.

NOTE: If removed, install the center Aft Engine Mount Inner Retainer Bracket.

Refer to SUBTASK 711060-400-001 002 If Removed, Install the Center

Aft Engine Mount Inner Retainer Bracket on Engine 1 .

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 73

5

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(2) Subtask 711060-832-002-002 - Detailed Inspection of the Aft Engine Mount Inner

Retainer Brackets for Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Fig. A-FFAAB

Flow Chart

Sheet 01

Fig. A-FBAAA

Inspection of the three Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

(a) At the threshold given in PLANNING INFORMATION paragraph E.(2):

Do a detailed inspection of the left, center and right Aft Engine Mount Inner

Retainer Brackets for the Engine 2.

Refer to Fig. A-FFAAB

NOTE: Identify the most visible surfaces of each Aft Engine Mount Inner

Retainer Brackets and clean these areas before performing the

detailed inspection.

NOTE: Use 10x magnifier, mirror and light to inspect the left, center and

right Aft Engine Mount Inner Retainer Brackets.

NOTE: The center Aft Engine Mount Inner Retainer Bracket may be difficult

to inspect visually, then an articulated fiberscope can be used as a

help. In case of doubt, remove the center Aft Engine Mount Inner

Retainer Bracket for inspection.

Refer to SUBTASK 711060-000-002 002 If necessary, Remove the

Center Aft Engine Mount Inner Retainer Bracket on Engine 2 .

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 74

5

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1 If AOT A71N001-12 is performed and dull Aft Engine Mount Inner Retainer

Brackets are replaced:

a Do a detailed inspection of the left, center and right Aft Engine Mount

Inner Retainer Brackets for the Engine 2.

Refer to Fig. A-FBAAA

<1> If any Inner Retainer Bracket is found damaged, cracked, broken or

missing:

<a> Before next flight, replace as required the affected

Inner Retainer Bracket, in accordance with SUBTASK

711060-000-002 002 If necessary, Remove the Center Aft

Engine Mount Inner Retainer Bracket on Engine 2 thru

SUBTASK 711060-000-006 002 If necessary, Remove the

Right Aft Engine Mount Inner Retainer Bracket on Engine 2 for

the removal and SUBTASK 711060-400-002 002 If Removed,

Install the Center Aft Engine Mount Inner Retainer Bracket on

Engine 2 thru SUBTASK 711060-400-006 002 If Removed,

Install the Right Aft Engine Mount Inner Retainer Bracket on

Engine 2 for the installation.

<b> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 2 at the

interval given in PLANNING INFORMATION paragraph E.(2).

<2> If Inner Retainer Brackets are not found damaged, cracked, broken

or missing:

<a> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 2 at the

interval given in PLANNING INFORMATION paragraph E.(2).

b Send the Inspection Report to AIRBUS, refer to Fig. A-FRAAA.

2 If AOT A71N001-12 is not performed and dull Aft Engine Mount Inner Retainer

Brackets are not replaced:

a Before next flight, replace as required the affected dull Inner Retainer

Bracket, in accordance with SUBTASK 711060-000-002 002 If necessary,

Remove the Center Aft Engine Mount Inner Retainer Bracket on Engine 2

thru SUBTASK 711060-000-006 002 If necessary, Remove the Right

Aft Engine Mount Inner Retainer Bracket on Engine 2 for the removal

and SUBTASK 711060-400-002 002 If Removed, Install the Center Aft

Engine Mount Inner Retainer Bracket on Engine 2 thru SUBTASK

711060-400-006 002 If Removed, Install the Right Aft Engine Mount

Inner Retainer Bracket on Engine 2 for the installation.

and

Do a detailed inspection of the left, center and right Aft Engine Mount

Inner Retainer Brackets for the Engine 2.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 75

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Refer to Fig. A-FBAAA

<1> If any Inner Retainer Bracket is found damaged, cracked, broken or

missing:

<a> Before next flight, replace as required the affected

Inner Retainer Bracket, in accordance with SUBTASK

711060-000-002 002 If necessary, Remove the Center Aft

Engine Mount Inner Retainer Bracket on Engine 2 thru

SUBTASK 711060-000-006 002 If necessary, Remove the

Right Aft Engine Mount Inner Retainer Bracket on Engine 2 for

the removal and SUBTASK 711060-400-002 002 If Removed,

Install the Center Aft Engine Mount Inner Retainer Bracket on

Engine 2 thru SUBTASK 711060-400-006 002 If Removed,

Install the Right Aft Engine Mount Inner Retainer Bracket on

Engine 2 for the installation.

<b> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 2 at the

interval given in PLANNING INFORMATION paragraph E.(2).

<2> If Inner Retainer Brackets are not found damaged, cracked, broken

or missing:

<a> Repeat the detailed inspection of the left, center and right Aft

Engine Mount Inner Retainer Brackets on the engine 2 at the

interval given in PLANNING INFORMATION paragraph E.(2).

b Send the Inspection Report to AIRBUS, refer to Fig. A-FRAAA.

NOTE: If removed, install the center Aft Engine Mount Inner Retainer Bracket.

Refer to SUBTASK 711060-400-002 002 If Removed, Install the Center

Aft Engine Mount Inner Retainer Bracket on Engine 2 .

(3) Subtask 711060-000-001-002 - If necessary, Remove the Center Aft Engine Mount

Inner Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-043

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 76

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SERVICE BULLETIN

References

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Without using the engine bootstrap system, remove the Center Aft Engine Mount

Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

2 Bolt Item (6) Retain

2 Washer Item (7) Retain

2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

2 Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system

to support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

- Do the Job Set-up procedure paragraph (3.E Installation of

the Bootstrap System) as specified in the Removal of the Aft

Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-000-043 and continue to the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

3 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 77

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attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

NOTE: Do not remove the pins Item (1) and (2) and the anti-rotation

bracket Item (3) from the link assembly Item (5) when you

remove the nuts Item (10) and (11).

(4) Subtask 711060-000-003-002 - If necessary, Remove the Left Aft Engine Mount

Inner Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 438AR, Door 451AL, Door 452AR, Door

437AL

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-043

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Without using the engine bootstrap system, remove the Left Aft Engine Mount Inner

Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

2 Bolt Item (6) Retain

2 Washer Item (7) Retain

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 78

5

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2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system to

support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

- Do the Job Set-up procedure paragraph 3.E Installation of the Bootstrap

System as specified in the Removal of the Aft Engine Mount Without

Engine Removal, refer to AMM Task 71-22-11-000-043 and continue to

the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

2 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

NOTE: Do not remove the pins Item (1) and (2) and the anti-rotation

bracket Item (3) from the link assembly Item (5) when you

remove the nuts Item (10) and (11).

(5) Subtask 711060-000-004-002 - If necessary, Remove the Right Aft Engine Mount

Inner Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 79

5

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References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-043

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Without using the engine bootstrap system, remove the Right Aft Engine Mount

Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

2 Bolt Item (6) Retain

2 Washer Item (7) Retain

2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system to

support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

- Do the Job Set-up procedure paragraph 3.E Installation of the Bootstrap

System as specified in the Removal of the Aft Engine Mount Without

Engine Removal, refer to AMM Task 71-22-11-000-043 and continue to

the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 80

5

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2 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

NOTE: Do not remove the pins Item (1) and (2) and the anti-rotation

bracket Item (3) from the link assembly Item (5) when you

remove the nuts Item (10) and (11).

(6) Subtask 711060-000-002-002 - If necessary, Remove the Center Aft Engine Mount

Inner Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-043

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Without using the engine bootstrap system, remove the Center Aft Engine Mount

Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 81

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2 Bolt Item (6) Retain

2 Washer Item (7) Retain

2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

2 Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system

to support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

- Do the Job Set-up procedure paragraph (3.E Installation of

the Bootstrap System) as specified in the Removal of the Aft

Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-000-043 and continue to the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

3 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

NOTE: Do not remove the pins Item (1) and (2) and the anti-rotation

bracket Item (3) from the link assembly Item (5) when you

remove the nuts Item (10) and (11).

(7) Subtask 711060-000-005-002 - If necessary, Remove the Left Aft Engine Mount

Inner Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 82

5

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Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-043

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Without using the engine bootstrap system, remove the Left Aft Engine Mount Inner

Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

2 Bolt Item (6) Retain

2 Washer Item (7) Retain

2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

2 Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system

to support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 83

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- Do the Job Set-up procedure paragraph 3.E Installation of

the Bootstrap System as specified in the Removal of the Aft

Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-000-043 and continue to the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

3 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

NOTE: Do not remove the pins Item (1) and (2) and the anti-rotation

bracket Item (3) from the link assembly Item (5) when you

remove the nuts Item (10) and (11).

(8) Subtask 711060-000-006-002 - If necessary, Remove the Right Aft Engine Mount

Inner Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-000-043

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Without using the engine bootstrap system, remove the Right Aft Engine Mount

Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 84

5

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@A318/A319/A320/A321

SERVICE BULLETIN

1 Remove the outer retainer brackets:

1 Outer Retainer Bracket Item (9) Retain

and

1 Outer Retainer Bracket Item (12) Retain

attached with:

2 Bolt Item (6) Retain

2 Washer Item (7) Retain

2 Washer Item (13) Retain

2 Nut Item (14) Retain

NOTE: If the inner retainer bracket is found broken, do a torque check

of the nuts Item (10) and (11) in accordance with SUBTASK

711060-831-001 001 Torque check .

Check the gap between the pin head item (2) and the anti-rotation bracket

item (3).

a If the gap is more than 0.025 mm (0.001 in.), install the bootstrap system to

support the Engine weight:

Refer to Fig. A-FBBAA Sheet 02

- Do the Job Set-up procedure paragraph 3.E Installation of the Bootstrap

System as specified in the Removal of the Aft Engine Mount Without

Engine Removal, refer to AMM Task 71-22-11-000-043 and continue to

the next step.

b If the gap is less than 0.025 mm (0.001 in.), continue to the next step.

2 Remove the Inner Retainer Bracket:

1 Inner Retainer Bracket Item (8) Discard

attached with:

1 Nut Item (11) Retain

1 Nut Item (10) Retain

NOTE: Do not remove the pins Item (1) and Item (2) and the antirotation bracket Item (3) from the link assembly Item (5) when

you remove the nuts Item (10) and Item (11).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 85

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

(9) Subtask 711060-400-001-002 - If Removed, Install the Center Aft Engine Mount

Inner Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-043

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Center Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 86

5

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SERVICE BULLETIN

- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum torque

value of 12.88 m.daN (95.00 lbf.ft).

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

NOTE: Do not torque the nut Item 11 more than the maximum torque

value of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 87

5

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@A318/A319/A320/A321

SERVICE BULLETIN

2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-043.

(10) Subtask 711060-400-003-002 - If Removed, Install the Left Aft Engine Mount Inner

Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-043

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 88

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

References

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Left Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum value

of 12.88 m.daN (95.00 lbf.ft).

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 89

5

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@A318/A319/A320/A321

SERVICE BULLETIN

NOTE: Do not torque the nut Item 11 more than the maximum value

of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-043.

(11) Subtask 711060-400-004-002 - If Removed, Install the Right Aft Engine Mount Inner

Retainer Bracket on Engine 1

Work Zones and Access Panels

Zone Access/Work location

450 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 90

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-043

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Right Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum value

of 12.88 m.daN (95.00 lbf.ft).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 91

5

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@A318/A319/A320/A321

SERVICE BULLETIN

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

NOTE: Do not torque the nut Item 11 more than the maximum value

of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-043.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 92

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

(12) Subtask 711060-400-002-002 - If Removed, Install the Center Aft Engine Mount

Inner Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-043

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Center Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 93

5

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SERVICE BULLETIN

- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum value

of 12.88 m.daN (95.00 lbf.ft).

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

NOTE: Do not torque the nut Item 11 more than the maximum value

of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 94

5

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SERVICE BULLETIN

2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-043.

(13) Subtask 711060-400-005-002 - If Removed, Install the Left Aft Engine Mount Inner

Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 437AL, Door 438AR, Door 451AL, Door

452AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-043

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 95

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

References

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Left Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum value

of 12.88 m.daN (95.00 lbf.ft).

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 96

5

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@A318/A319/A320/A321

SERVICE BULLETIN

NOTE: Do not torque the nut Item 10 more than the maximum value

of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-043.

(14) Subtask 711060-400-006-002 - If Removed, Install the Right Aft Engine Mount Inner

Retainer Bracket on Engine 2

Work Zones and Access Panels

Zone Access/Work location

460 Access Door 447AL, Door 448AR, Door 461AL, Door

462AR

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills ENGINE

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 97

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

Material necessary to do the job

Equipment BFEA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

8 238-0252-505 1 RETAINER (1)

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

NOTE (1): The components listed above are only necessary if the Inner Retainer

Bracket is found nonconforming dull, missing, damaged, cracked or

broken. The quantity of these items are to be ordered as required.

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Task 71-22-11-400-043

Fig. A-FBBAA

Replacement of the Left, Center and

Right Aft Engine Mount Inner Retainer

Brackets

Sheet 01

Sheet 02

(a) Install the Right Aft Engine Mount Inner Retainer Bracket:

Refer to Fig. A-FBBAA

Refer to AMM Task 20-21-11-911-001

1 Install on the link assembly Item (5) and on the pin Item (2):

1 Inner Retainer Bracket 238-0252-505 Item 8

with:

1 Nut Item (10) Retained at

removal

- Tighten the nut Item (10) to a torque value between 10.85 m.daN (80.00

lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (9) Retained at

removal

- Record the position necessary for the alignment of the nut Item (10).

- Increase the torque on the nut Item (10) as necessary to align the nut

Item (10) with the outer retainer bracket Item (9).

NOTE: Do not torque the nut Item 10 more than the maximum value

of 12.88 m.daN (95.00 lbf.ft).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 98

5

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@A318/A319/A320/A321

SERVICE BULLETIN

2 Install on the pin Item (1):

1 Nut Item (11) Retained at

removal

- Tighten the nut Item (11) to a torque value between 4.75 m.daN (35.00

lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

- Temporarily install:

1 Outer Retainer Bracket Item (12) Retained at

removal

- Record the position necessary for the alignment of the nut Item (11).

- Increase the torque on the nut Item (11) as necessary to align the nut

Item (11) with the outer retainer bracket Item (12).

NOTE: Do not torque the nut Item 11 more than the maximum value

of 5.69 m.daN (42.00 lbf.ft).

3 Fasten on the Inner Retainer Bracket Item 8:

1 Outer Retainer Bracket Item (9) Retained at

removal

1 Outer Retainer Bracket Item (12) Retained at

removal

with:

2 Bolt Item (6) Retained at

removal

2 Washer Item (7) Retained at

removal

2 Washer Item (13) Retained at

removal

2 Nut Item (14) Retained at

removal

- Tighten the nut Item (14) to a torque value between 0.27 m.daN (24.00

lbf.in.) and 0.31 m.daN (27.00 lbf.in.).

NOTE: Check the self-locking feature of the nut Item (14) before use

again to ensure the minimum breakaway torque.

4 If installed, remove the bootstrap system:

- Do the Close-up procedure paragraph 5.A as specified in the Installation

of the Aft Engine Mount Without Engine Removal, refer to AMM Task

71-22-11-400-043.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 99

5

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@A318/A319/A320/A321

SERVICE BULLETIN

(15) Subtask 711060-831-001-001 - Torque check

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

NOTE: Before starting the torque check, apply two lines of ink across nuts Item

(10) and (11) to bolts Item (1) and (2).

(a) Check the existing torque by turning the nuts counter-clockwise slowly in the

removal direction until the point of torque release.

NOTE: Check the torque of the nuts Item (10) and (11), by using a torque

wrench with an open-end type adapter or a torque wrench with a

socket. The socket can be no longer than 51.51 mm (2.04 in.).

(b) Re-torque the nut Item (10) to match the ink lines and read the torque. The torque

value must be between 10.85 m.daN (80.00 lbf.ft) and 12.88 m.daN (95.00 lbf.ft).

NOTE: Make sure the pin head is aligned with the slot in the retainer prior

to re-torque.

(c) Re-torque the nut Item (11) to match the ink lines and read the torque. The torque

value must be between 4.75 m.daN (35.00 lbf.ft) and 5.69 m.daN (42.00 lbf.ft).

NOTE: Make sure the pin head is aligned with the slot in the retainer prior

to re-torque.

(d) If the nut torque is incorrect contact AIRBUS for reporting purpose.

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 100

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**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 711060-942-001-001 - Close-up for Engine 1

Work Zones and Access Panels

Zone Access/Work location

450

Manpower Resources

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 71-13-00-410-040

Task 78-36-00-410-040

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the Thrust Reverser Doors, refer to AMM Task 78-36-00-410-040.

(c) Close the Fan Cowl Doors, refer to AMM Task 71-13-00-410-040.

(d) Remove the access platform(s).

(e) Put the aircraft back to its initial configuration.

(2) Subtask 711060-942-002-001 - Close-up for Engine 2

Work Zones and Access Panels

Zone Access/Work location

460

Manpower Resources

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 71-13-00-410-040

Task 78-36-00-410-040

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the Thrust Reverser Doors, refer to AMM Task 78-36-00-410-040.

(c) Close the Fan Cowl Doors, refer to AMM Task 71-13-00-410-040.

(d) Remove the access platform(s).

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 101

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(e) Put the aircraft back to its initial configuration.

**CONF 002

(1) Subtask 711060-942-001-001 - Close-up for Engine 1

Work Zones and Access Panels

Zone Access/Work location

450

Manpower Resources

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 71-13-00-410-040

Task 78-36-00-410-040

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the Thrust Reverser Doors, refer to AMM Task 78-36-00-410-040.

(c) Close the Fan Cowl Doors, refer to AMM Task 71-13-00-410-040.

(d) Remove the access platform(s).

(e) Put the aircraft back to its initial configuration.

(2) Subtask 711060-942-002-001 - Close-up for Engine 2

Work Zones and Access Panels

Zone Access/Work location

460

Manpower Resources

Skills ENGINE

References

Aircraft Maintenance Manual (AMM) Task 71-13-00-410-040

Task 78-36-00-410-040

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the Thrust Reverser Doors, refer to AMM Task 78-36-00-410-040.

(c) Close the Fan Cowl Doors, refer to AMM Task 71-13-00-410-040.

(d) Remove the access platform(s).

(e) Put the aircraft back to its initial configuration.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 102

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**CONF ALL

A

A

A

LH SHOWN

RH SYMETRICAL

B

TYPICAL

NOTE:

INNER RETAINER BRACKET TO BE INSPECTED

IDENTIFY THE MOST VISIBLE SURFACES AND

CLEAN THESE AREAS BEFORE THE INSPECTION

B

C

N_SB_711060_5_BAAA_01_03

Figure A-FBAAA - Sheet 01

Inspection of the three Left, Center and Right Aft Engine Mount Inner Retainer Brackets

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 103

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**CONF ALL

NOTE:

USE 10X MAGNIFIER AND MIRROR AND LIGHT TO INSPECT THE SURFACE FINISH OF THE THREE 

RETAINER BRACKETS

NORMAL BRIGHT SMOOTH SURFACE NONCONFORMING DULL PITTED SURFACE

TYPICAL

C

N_SB_711060_5_BAAA_02_01

Figure A-FBAAA - Sheet 02

Inspection of the three Left, Center and Right Aft Engine Mount Inner Retainer Brackets

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 104

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**CONF ALL

(6)

(7)

(10)

(11)

(14)

(13)

(12)

(9)

02

03

01

(2)

(3)

(5)

(1)

LH SHOWN

RH SYMMETRICAL

TYPICAL

B

A

A

NOTE:

01

02 TIGHTEN THE NUT ITEM (10) TO A TORQUE VALUE BETWEEN 10.85 m.daN (80.00 lbf.ft) 

AND 12.88 m.daN (95.00 lbf.ft)

03 TIGHTEN THE NUT ITEM (11) TO A TORQUE VALUE BETWEEN 4.75 m.daN (35.00 lbf.ft) 

AND 5.69 m.daN (42.00 lbf.ft)

TIGHTEN THE NUT ITEM (14) TO A TORQUE VALUE BETWEEN 0.27 m.daN (24.00 lbf.in) 

AND 0.31 m.daN (27.00 lbf.in)

B

x3

x3

x3

x3

x3

x3

8

(8)

x3

x3

x3

x3

x3

x3 x3

x3

A

C

N_SB_711060_5_BBAA_01_03

Figure A-FBBAA - Sheet 01

Replacement of the Left, Center and Right Aft Engine Mount Inner Retainer Brackets

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 105

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**CONF ALL

NOTE:

04 INSPECT THE GAP BETWEEN THE PIN HEAD ITEM (2) AND THE ANTI−ROTATION BRACKET ITEM (3)

AT THE AFT ENGINE MOUNT BEAM

04

AFT ENGINE MOUNT BEAM

TYPICAL

C

0.025 mm

(0.001 in)

THE GAP MUST BE LESS THAN 0.025 mm (0.001 in)

(2)

(1)

(3)

(5)

N_SB_711060_5_BBAA_02_03

Figure A-FBBAA - Sheet 02

Replacement of the Left, Center and Right Aft Engine Mount Inner Retainer Brackets

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 106

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**CONF 001

 AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2)

DO A DETAILED INSPECTION OF THE AFT ENGINE MOUNT INNER RETAINER BRACKETS

FOR ENGINE 1 AND ENGINE 2 (IN ACCORDANCE WITH TASK 711060−832−801−001)

YES

NO

REPLACE THE DULL RETAINER BRACKET(S)

ON ENGINE 1 AND/OR ENGINE 2 

 (IN ACCORDANCE WITH SUBTASK 711060−

000−001−001 THRU SUBTASK 711060−000−006−

001 FOR THE REMOVAL AND SUBTASK 711060−

400−001−001 THRU SUBTASK 711060−400−006−

AOT A71N001−12

PERFORMED AND DULL

RETAINER BRACKETS

REPLACED

DO A DETAILED INSPECTION OF THE AFT ENGINE

MOUNT INNER RETAINER BRACKETS

 (IN ACCORDANCE WITH SUBTASK 711060−832−001−001 

FOR ENGINE 1 AND SUBTASK 711060−832−002−001 FOR ENGINE 2)

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

RETAINER BRACKET

FOUND DAMAGED, CRACKED

BROKEN OR MISSING

QUESTION ACTION FINDING

REPEAT THE DETAILED INSPECTION OF THE AFT ENGINE

MOUNT INNER RETAINER BRACKETS FOR ENGINE 1 AND ENGINE 2

 (IN ACCORDANCE WITH TASK 711060−832−801−001) AT THE INTERVAL

GIVEN IN THE PLANNING INFORMATION PARAGRAPH E. (2)

YES

BEFORE NEXT FLIGHT, REPLACE THE

AFFECTED RETAINER BRACKET(S)

ON ENGINE 1 AND/OR ENGINE 2 (IN

ACCORDANCE WITH SUBTASK 711060−

NO

001 FOR THE INSTALLATION) BEFORE 

000−001−001 THRU SUBTASK 711060−

000−006−001 FOR THE REMOVAL AND 

SUBTASK 711060−400−001−001 THRU

SUBTASK 711060−400−006−001 FOR THE

INSTALLATION) AND CONTACT AIRBUS

NEXT FLIGHT

N_SB_711060_5_FAAA_01_04

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 107

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**CONF 002

 AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2)

DO A DETAILED INSPECTION OF THE AFT ENGINE MOUNT INNER RETAINER BRACKETS

FOR ENGINE 1 AND ENGINE 2 (IN ACCORDANCE WITH TASK 711060−832−801−001)

YES

NO

REPLACE THE DULL RETAINER BRACKET(S)

ON ENGINE 1 AND/OR ENGINE 2 

 (IN ACCORDANCE WITH SUBTASK 711060−

000−001−002 THRU SUBTASK 711060−000−006−

002 FOR THE REMOVAL AND SUBTASK 711060−

400−001−002 THRU SUBTASK 711060−400−006−

AOT A71N001−12

PERFORMED AND DULL

RETAINER BRACKETS

REPLACED

DO A DETAILED INSPECTION OF THE AFT ENGINE

MOUNT INNER RETAINER BRACKETS

 (IN ACCORDANCE WITH SUBTASK 711060−832−001−002 

FOR ENGINE 1 AND SUBTASK 711060−832−002−002 FOR ENGINE 2)

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

RETAINER BRACKET

FOUND DAMAGED, CRACKED

BROKEN OR MISSING

QUESTION ACTION FINDING

REPEAT THE DETAILED INSPECTION OF THE AFT ENGINE

MOUNT INNER RETAINER BRACKETS FOR ENGINE 1 AND ENGINE 2

 (IN ACCORDANCE WITH TASK 711060−832−801−001) AT THE INTERVAL

GIVEN IN THE PLANNING INFORMATION PARAGRAPH E. (2)

YES

BEFORE NEXT FLIGHT, REPLACE THE

AFFECTED RETAINER BRACKET(S)

ON ENGINE 1 AND/OR ENGINE 2 (IN

ACCORDANCE WITH SUBTASK 711060−

NO

002 FOR THE INSTALLATION) BEFORE 

000−001−002 THRU SUBTASK 711060−

000−006−002 FOR THE REMOVAL AND 

SUBTASK 711060−400−001−002 THRU

SUBTASK 711060−400−006−002 FOR THE

INSTALLATION) AND CONTACT AIRBUS

NEXT FLIGHT

N_SB_711060_5_FAAB_01_03

Figure A-FFAAB - Sheet 01

Flow Chart

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 108

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SERVICE BULLETIN

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−71−1060

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEEE6

NACELLE SYSTEMS AND STRUCTURE

INSPECTION METHOD :

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX: +33 (0)5 61 93 36 14 DETAILED

INSPECTION

A

A

A

LH SHOWN

RH SYMMETRICAL

B

TYPICAL

B

INNER RETAINER BRACKET

LEFT

CENTER

RIGHT

N_SB_711060_5_RAAA_01_01

Figure A-FRAAA - Sheet 01

Inspection Report

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 109

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**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−71−1060

DATE OF INSPECTION :

INSPECTION METHOD : DETAILED

INSPECTION

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEEE6

NACELLE SYSTEMS & STRUCTURE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

INNER

BRACKET

YES NO

AOT A71N001−12

YES NO

YES NO

REMARKS

ENGINE 1

YES NO

YES NO

YES NO

YES NO

YES NO

YES NO

YES NO

YES NO

YES NO

RETAINER

PERFORMED

DULL INNER

RETAINER

REPLACED

INNER RETAINER

BRACKET FOUND

DAMAGED,

CRACKED, BROKEN

OR MISSING

RETAINER

BRACKET

REPLACED

YES NO

AOT A71N001−12

YES NO

YES NO

REMARKS

ENGINE 2

YES NO

YES NO

YES NO

YES NO

YES NO

YES NO

YES NO

YES NO

YES NO

PERFORMED

DULL INNER

RETAINER

BRACKET

INNER RETAINER

BRACKET FOUND

DAMAGED,

CRACKED, BROKEN

OR MISSING

RETAINER

BRACKET

REPLACED

BRACKET

INNER

REPLACED

INNER

LEFT

INNER

BRACKET

RETAINER

CENTER

INNER

BRACKET

RETAINER

RIGHT

INNER

BRACKET

RETAINER

LEFT

INNER

BRACKET

RETAINER

CENTER

INNER

BRACKET

RETAINER

RIGHT

N_SB_711060_5_RAAA_02_01

Figure A-FRAAA - Sheet 02

Inspection Report

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 110

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SERVICE BULLETIN

Appendix 01 - Elapsed Time Assumption

**CONF ALL

(1) For an explanation of the manhours and elapsed time, refer to the following Gantt Chart.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 1

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Appendix 01 - Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No A320−71−1060

ELAPSED TIME

(HOURS)

MH:

ET:

PER:

MANHOURS

ELAPSED TIME

NUMBER OF PERSONS

TOTAL MANHOURS (MH)

ELAPSED TIME (ET)

3.00

1.50

STEPS

0 0.5 1 1.5

GET ACCESS 1.00 2 0.50

DETAILED INSPECTION

OF THE AFT ENGINE

CLOSE−UP

0.50 1 0.50

0.50 1 0.50

1.00 2 0.50

MOUNT INNER

 RETAINER BRACKETS

FOR ENGINE 1

DETAILED INSPECTION

OF THE AFT ENGINE

MOUNT INNER

 RETAINER BRACKETS

FOR ENGINE 2

01

02

THIS CHART IS ONLY A PROPOSAL

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM

01

02

NOTE:

IF A VSB IS INVOLVED THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART

MH PER ET/S

N_SB_711060_5_AAAA_01_02

Figure A-FAAAA - Sheet 01

Gantt Chart

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 2

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SERVICE BULLETIN

REPORTING SHEET

TITLE: POWER PLANT GENERAL - AFT ENGINE MOUNT INSTL - INSPECTION

OF AFT ENGINE MOUNT INNER RETAINER BRACKET FOR CFM56-5A/-

5B ENGINES.

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Oct 09/14 SERVICE BULLETIN No.: A320-71-1060

REVISION No.: 01 - Apr 07/15 Page: 1

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